[Federal Register: March 18, 2003 (Volume 68, Number 52)]
[Rules and Regulations]
[Page 12802-12806]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr18mr03-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-216-AD; Amendment 39-12912; AD 2002-21-06]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9-81 (MD-
81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; correction.
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SUMMARY: This document corrects information in an existing
airworthiness directive (AD) that applies to all McDonnell Douglas
Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-
87), and MD-88 airplanes. That AD currently requires revisions to the
Airplane Flight Manual; installation of inspection aids on the wing
upper surfaces; and, among other actions, installation of an overwing
heater blanket system or primary upper wing ice detection system, and
installation of a heater protection panel or an equipment protection
device on certain overwing heater blanket systems. That AD also
requires disabling the anti-ice systems for the upper wing surface on
certain airplanes. This document corrects a reference to an incorrect
paragraph. This correction is necessary to provide the correct
paragraph reference.
DATES: Effective November 8, 2002.
The incorporation by reference of certain publications listed in
the regulations was approved previously by the Director of the Federal
Register as of November 8, 2002 (67 FR 65298, October 24, 2002).
The incorporation by reference of certain publications, as listed
in the regulations, was approved previously by the Director of the
Federal Register as January 17, 1992 (57 FR 2014, January 17, 1992).
The incorporation by reference of certain other publications, as
listed in the regulations, was approved previously by the Director of
the Federal Register as of May 7, 2001 (66 FR 17499, April 2, 2001).
FOR FURTHER INFORMATION CONTACT: Technical Information: Cheyenne Del
Carmen, Aerospace Engineer, Systems and Equipment Branch, ANM-130L,
FAA, Los Angeles Aircraft Certification Office, 3960 Paramount
Boulevard, Lakewood, California 90712-4137; telephone (562) 627-5338;
fax (562) 627-5210.
Other Information: Judy Golder, Airworthiness Directive Technical
Editor/Writer; telephone (425) 687-4241, fax (425) 227-1232. Questions
or comments may also be sent via the Internet using the following
address: judy.golder@faa.gov. Questions or comments sent via the
Internet as attached electronic files must be formatted in Microsoft
Word 97 for Windows or ASCII text.
SUPPLEMENTARY INFORMATION: On October 9, 2002, the Federal Aviation
Administration (FAA) issued AD 2002-21-06, amendment 39-12912 (67 FR
65298, October 24, 2002), which applies to all McDonnell Douglas Model
DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and
MD-88 airplanes. That AD requires revisions to the Airplane Flight
Manual; installation of inspection aids on the wing upper surfaces;
and, among other actions, installation of an overwing heater blanket
system or primary upper wing ice detection system, and installation of
a heater protection panel or an equipment protection device on certain
overwing heater blanket systems. That AD also requires disabling the
anti-ice systems for the upper wing surface on certain airplanes. The
actions required by that AD are intended to prevent ice ingestion into
one or both engines and consequent loss of thrust from one or both
engines; and damage to the upper wing skin surface and its structure,
due to prolonged short-circuit electrical arcing of certain anti-ice
systems.
On December 23, 2002, the FAA issued AD 2002-21-06 COR, amendment
39-12912 (68 FR 5, January 2, 2003), that corrected certain references
that were transposed in two paragraphs.
Need for the Correction
After publication of that correction, the FAA received comments
from two operators that point out the need for further correction. One
commenter notes that, in the corrected AD, the statement at the
beginning of the body advising that AD 2002-21-06 supersedes AD 2001-
06-16 COR, amendment 39-12163, is missing. The commenter states that
adding that statement would clarify that AD 2001-06-16 has been
superseded. Both
[[Page 12803]]
commenters also note that in paragraph (l)(2)(i) of the originally
corrected AD, having the heading of ``Alternate Methods of Compliance
(AMOC),'' reference is made to installation of a non-skid, striped
triangular symbol per option 5 of McDonnell Douglas Service Bulletin
MD80-30-059, Revision 4 through Revision 7, as being approved as AMOCs
with paragraphs (c) and (i)(2) of the originally corrected AD. The
commenters point out that the correct reference should be ``with
paragraphs (c) and (i)(4) of the AD.''
The FAA agrees with the commenters that clarification and
correction are necessary and has determined a need for the issuance of
a second correction of AD 2002-21-06. This correction adds the
statement, which was inadvertently omitted, at the beginning of the AD
advising that AD 2002-21-06 supersedes AD 2001-06-16 COR. This
correction will also revise paragraph (l)(2)(i) of the AD to reference
the correct paragraphs, i.e., paragraphs (c) and (i)(4) of the AD.
Correction of Publication
This document corrects the errors and correctly adds the AD as an
amendment to section 39.13 of the Federal Aviation Regulations (14 CFR
39.13).
The AD is reprinted in its entirety for the convenience of affected
operators. The effective date of the AD remains November 8, 2002.
Since this action only adds clarifying information and corrects a
typographical error in a paragraph reference, it has no adverse
economic impact and imposes no additional burden on any person.
Therefore, the FAA has determined that notice and public procedures are
unnecessary.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Correction
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Corrected]
2. Section 39.13 is amended by correctly adding the following
airworthiness directive (AD):
2002-21-06 McDonnell Douglas: Amendment 39-12912. Docket 2002-NM-
216-AD. Supersedes AD 2001-06-16 COR, Amendment 39-12163.
Applicability: All Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-
83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes; certificated in
any category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (l)(1)
of this AD. The request should include an assessment of the effect
of the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent damage to the upper wing skin surface and its
structure, due to prolonged short-circuit electrical arcing of the
anti-ice system; accomplish the following:
Restatement of Requirements of AD 2001-06-16 COR
Airplane Flight Manual Revision
(a) Within 10 days after January 17, 1992 (the effective date of
AD 92-03-02, amendment 39-8156), revise the Limitations Section of
the FAA-approved Airplane Flight Manual (AFM) to include the
following. This may be accomplished by inserting a copy of this AD
in the AFM.
``Ice on Wing Upper Surfaces
Caution
Ice shedding from the wing upper surface during takeoff can
cause severe damage to one or both engines, leading to surge,
vibration, and complete thrust loss. The formation of ice can occur
on wing surfaces during exposure of the airplane to normal icing
conditions. Clear ice can also occur on the wing upper surfaces when
cold-soaked fuel is in the main wing fuel tanks, and the airplane is
exposed to conditions of high humidity, rain, drizzle, or fog at
ambient temperatures well above freezing. Often, the ice
accumulation is clear and difficult to detect visually. The ice
forms most frequently on the inboard, aft corner of the main wing
tanks. [End of Cautionary Note].
The wing upper surfaces must be physically checked for ice when the
airplane has been exposed to conditions conducive to ice formation.
Takeoff may not be initiated unless the flight crew verifies that a
visual check and a physical (hands-on) check of the wing upper
surfaces have been accomplished, and that the wing is clear of ice
accumulation when any of the following conditions occur:
(1) When the ambient temperature is less than 50 degrees F and
high humidity or visible moisture (rain, drizzle, sleet, snow, fog,
etc.) is present;
(2) When frost or ice is present on the lower surface of either
wing;
(3) After completion of de-icing.
When inspection aids (i.e. tufts, decals, mount pads, painted
symbols, and paint stripes) are installed in accordance with
McDonnell Douglas MD-80 Service Bulletin 30-59, the physical check
may be made by assuring that all installed tufts move freely.
Note: This limitation does not relieve the requirement that
aircraft surfaces are free of frost, snow, and ice accumulation, as
required by Federal Aviation Regulations Sections 91.527 and
121.629. [End of Note]''
AFM Configuration Deviation List Revision
(b) Within 10 days after January 17, 1992, revise the
Configuration Deviation List (CDL) Appendix of the FAA-approved AFM
to include the following. This may be accomplished by inserting a
copy of this AD in the AFM.
``30-80-01 Triangular Decal and Tuft Assemblies
Up to two (2) decals or tufts per side may be missing, provided:
(a) At least one decal and tuft on each side is located along
the aft spar line; and
(b) The tufts are used for performing the physical check to
determine that the upper wing is free of ice by observing that the
tufts move freely.
Up to eight (8) decals and/or tufts may be missing, provided:
(a) Takeoff may not be initiated unless the flight crew verifies
that a physical (hands-on) check is made of the upper wing in the
location of the missing decals and/or tufts to assure that there is
no ice on the wing when icing conditions exist;
or
(b) When the ambient temperature is more than 50 degrees F.''
Installation of Inspection Aids
(c) Within 30 days after January 17, 1992, install inspection
aids (i.e., tufts, decals, mount pads, painted symbols, and paint
stripes) on the inboard side of the wings' upper surfaces, in
accordance with McDonnell Douglas Service Bulletin 30-59, dated
September 18, 1989; Revision 1, dated January 5, 1990; or Revision
2, dated August 15, 1990.
Repetitive Tests and One-Time Inspection
(d) For airplanes on which an overwing heater blanket system was
installed without installation of a heater protection panel (HPP) or
an equipment protection device (EPD) prior to May 7, 2001 (the
effective date of 2001-06-16 COR, amendment 39-12163): Within 60
days after May 7, 2001, accomplish the actions specified in
paragraph (d)(1) or (d)(2) of this AD, as applicable.
(1) For airplanes on which the overwing heater blanket system
was installed in accordance with McDonnell Douglas Service
[[Page 12804]]
Bulletin MD80-30-071, Revision 02, dated February 6, 1996; or
McDonnell Douglas Service Bulletin MD80-30-078, Revision 01, dated
April 8, 1997: Accomplish paragraphs (d)(1)(i) and (d)(1)(ii) of
this AD.
(i) Remove secondary access covers, and perform a one-time
detailed visual inspection to detect discrepancies (mechanical
damage or punctures in the upper skin of the blanket, prying damage
on the panel, and fuel leakage) of the overwing heater blanket, in
accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997. And,
(ii) Accomplish paragraph (d)(1)(ii)(A) or (d)(1)(ii)(B) of this
AD.
(A) Perform dielectric withstanding voltage and resistance tests
in accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997. Repeat the tests thereafter at
intervals not to exceed 150 days, until installation of an HPP in
accordance with paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as
applicable.
(B) Deactivate the overwing heater blanket system until
accomplishment of dielectric withstanding voltage and resistance
tests specified in paragraph (d)(1)(ii)(A). If the overwing heater
blanket system is deactivated as provided by this paragraph,
continue to accomplish the requirements of paragraphs (a), (b), and
(c) of this AD.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
(2) For airplanes on which the overwing heater blanket system
was installed in accordance with TDG Aerospace, Inc., STC SA6042NM:
Accomplish paragraphs (d)(2)(i) and (d)(2)(ii) of this AD.
(i) Remove secondary access covers, and perform a one-time
detailed visual inspection to detect discrepancies (mechanical
damage or punctures in the upper skin of the blanket, prying damage
on the panel, and fuel leakage) of the overwing heater blanket, in
accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997. And,
(ii) Accomplish paragraph (d)(2)(ii)(A) or (d)(2)(ii)(B) of this
AD.
(A) Perform dielectric withstanding voltage and resistance tests
in accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997. Repeat the tests thereafter at
intervals not to exceed 150 days, until installation of an EPD in
accordance with paragraph (f)(2)(i) of this AD.
(B) Deactivate overwing heater blanket system until
accomplishment of dielectric withstanding voltage and resistance
tests specified in paragraph (d)(2)(ii)(A). If the overwing heater
blanket system is deactivated as provided by this paragraph,
continue to accomplish the requirements of paragraphs (a), (b), and
(c) of this AD.
Corrective Action
(e) If any discrepancy is detected during any inspection or test
performed in accordance with paragraph (d) of this AD, prior to
further flight, repair or replace the affected heater blanket, in
accordance with McDonnell Douglas Alert Service Bulletin MD80-
30A087, dated September 22, 1997; except as provided in paragraph
(h) of this AD.
Note 3: McDonnell Douglas Alert Service Bulletin MD80-30A087,
dated September 22, 1997, references TDG Aerospace Document E95-451,
Revision B, dated January 31, 1996, as an additional source of
service information for accomplishment of repair or replacement of
the overwing heater blanket.
Installation of Overwing Heater Blanket or Primary Upper Wing Ice
Detection System
(f) Within 3 years after May 7, 2001, do the requirements of
either paragraph (f)(1) or (f)(2) of this AD.
(1) Do the actions specified in paragraph (f)(1)(i) or
(f)(1)(ii) of this AD, as applicable.
(i) For airplanes listed in Group 1 in McDonnell Douglas Service
Bulletin MD80-30-090, dated October 19, 1999: Install an overwing
heater blanket system in accordance with McDonnell Douglas Service
Bulletin MD80-30-071, Revision 02, dated February 6, 1996; and
modify and reidentify the existing HPP in accordance with McDonnell
Douglas Service Bulletin MD80-30-090. Modification of the existing
HPP in accordance with this paragraph constitutes terminating action
for the repetitive inspections required by (d)(1)(ii)(A) of this AD.
(ii) For airplanes listed in Group 2 in McDonnell Douglas
Service Bulletin MD80-30-090, dated October 19, 1999: Install an
overwing heater blanket system in accordance with McDonnell Douglas
Service Bulletin MD80-30-078, Revision 01, dated April 8, 1997; and
install an HPP and associated wiring in accordance with McDonnell
Douglas Service Bulletin MD80-30-090. Installation of an HPP and
associated wiring in accordance with this paragraph constitutes
terminating action for the repetitive inspections required by
(d)(1)(ii)(A) of this AD.
Note 4: For other airplanes, accomplishment of the requirements
of paragraph (f)(1)(i) or (f)(1)(ii) of this AD may be acceptable
per paragraph (i)(1) of this AD.
(2) Accomplish the actions specified in either paragraph
(f)(2)(i), (f)(2)(ii), or (f)(2)(iii) of this AD.
(i) Install an overwing heater blanket system, and install an
EPD that provides a circuit protection function to the overwing
heater blanket, in accordance with a method approved by the Manager,
Los Angeles Aircraft Certification Office (ACO), FAA. Installation
of an EPD in accordance with this paragraph constitutes terminating
action for the repetitive inspections required by (d)(2)(ii)(A) of
this AD.
Note 5: Installation of an overwing heater blanket system and
installation of an EPD that provides a circuit protection function
to the overwing heater blanket, in accordance with TDG Aerospace,
Inc., SA6042NM, or TDG Master Drawing List (MDL) E93-104, Revision
R, dated October 25, 2000; is an approved means of compliance with
the requirements of paragraph (f)(2)(i) of this AD.
(ii) Install an overwing heater blanket system in accordance
with a method approved by the Manager, Los Angeles ACO.
(iii) Install an FAA-approved primary upper wing ice detection
system in accordance with a method approved by the Manager, Los
Angeles ACO.
Note 6: Boeing (McDonnell Douglas) has received FAA approval of
a primary upper wing ice detection system that is considered to be
an alternative method of compliance (AMOC) with the requirements of
paragraph (f)(2)(iii) of this AD. Information concerning such AMOCs
may be obtained from the Los Angeles ACO.
AFM Revision
(g) Except as provided by paragraph (h) of this AD, prior to
further flight after accomplishment of the installation required by
paragraph (f)(1) or (f)(2) of this AD, revise the Limitations
Section of the FAA-approved AFM to include the following. This may
be accomplished by inserting a copy of this AD in the AFM. After
accomplishment of the installation required by paragraph (f)(1) or
(f)(2) of this AD and this AFM revision, the AFM revisions required
by paragraphs (a) and (b) of this AD may be removed from the AFM,
and the inspection aids required by paragraph (c) of this AD may be
removed from the airplane.
``Ice on Wing Upper Surfaces
Caution
Ice shedding from the wing upper surface during takeoff can
cause severe damage to one or both engines, leading to surge,
vibration, and complete thrust loss. The formation of ice can occur
on wing surfaces during exposure of the airplane to normal icing
conditions. Clear ice can also occur on the wing upper surfaces when
cold-soaked fuel is in the main wing fuel tanks, and the airplane is
exposed to conditions of high humidity, rain, drizzle, or fog at
ambient temperatures well above freezing. Often, the ice
accumulation is clear and difficult to detect visually. The ice
forms most frequently on the inboard, aft corner of the main wing
tanks. [End of Cautionary Note]''.
MMEL Provision
(h) An airplane may be operated with an inoperative overwing
heater blanket or primary upper wing ice detection system for 10
days per the Master Minimum Equipment List (MMEL), provided that the
actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this
AD are done before further flight.
(1) Revise the Limitations Section of the FAA-approved AFM to
include the following. This may be accomplished by inserting a copy
of this AD in the AFM.
``Ice on Wing Upper Surfaces
Caution
The wing upper surfaces must be physically checked for ice when
the airplane has been exposed to conditions conducive to
[[Page 12805]]
ice formation. Takeoff may not be initiated unless the flight crew
verifies that a visual check and a physical (hands-on) check of the
wing upper surfaces have been accomplished, and that the wing is
clear of ice accumulation when any of the following conditions
occur:
(1) When the ambient temperature is less than 50 degrees F and
high humidity or visible moisture (rain, drizzle, sleet, snow, fog,
etc.) is present;
(2) When frost or ice is present on the lower surface of either
wing;
(3) After completion of de-icing.
When inspection aids (i.e. tufts, decals, mount pads, painted
symbols, and paint stripes) are installed in accordance with
McDonnell Douglas MD-80 Service Bulletin 30-59, the physical check
may be made by assuring that all installed tufts move freely.
Note: This limitation does not relieve the requirement that
aircraft surfaces are free of frost, snow, and ice accumulation, as
required by Federal Aviation Regulations Sections 91.527 and
121.629. [End of Note]''.
(2) Revise the CDL Appendix of the FAA-approved AFM to include
the following. This may be accomplished by inserting a copy of this
AD in the AFM.
``30-80-01 Triangular Decal and Tuft Assemblies
Up to two (2) decals or tufts per side may be missing, provided:
(a) At least one decal and tuft on each side is located along
the aft spar line; and
(b) The tufts are used for performing the physical check to
determine that the upper wing is free of ice by observing that the
tufts move freely.
Up to eight (8) decals and/or tufts may be missing, provided:
(a) Takeoff may not be initiated unless the flight crew verifies
that a physical (hands-on) check is made of the upper wing in the
location of the missing decals and/or tufts to assure that there is
no ice on the wing when icing conditions exist;
or
(b) When the ambient temperature is more than 50 degrees F.''
(3) Install inspection aids (i.e., tufts, decals, mount pads,
painted symbols, and paint stripes) on the inboard side of the
wings' upper surfaces, in accordance with McDonnell Douglas Service
Bulletin 30-59, dated September 18, 1989; Revision 1, dated January
5, 1990; or Revision 2, dated August 15, 1990.
New Requirements of This AD
Note 7: The Honeywell Anti-Ice System specified in paragraphs
(i), (j), and (k) of this AD, is also known and specified as an
overwing heater blanket system installed in accordance with
AlliedSignal Supplemental Type Certificate (STC) STC SA6061NM.
For Airplanes Equipped With a Honeywell Anti-Ice System Installed
per STC SA6061NM
(i) For airplanes equipped with a Honeywell Anti-Ice System
installed per STC SA6061NM: Accomplish the actions specified in
paragraphs (i)(1), (i)(2), (i)(3), and (i)(4) of this AD, at the
times specified in those paragraphs.
(1) Within 72 hours after the effective date of this AD, disable
the Honeywell Anti-Ice System installed per STC SA6061NM, per
Honeywell Alert Service Bulletin 109XXXX-30-38, dated August 8,
2002.
(2) Within 72 hours after the effective date of this AD, revise
the Limitations Section of the FAA-approved AFM to include the
following (this may be accomplished by inserting a copy of this AD
in the AFM):
``Ice on Wing Upper Surfaces
Caution
Ice shedding from the wing upper surface during takeoff can
cause severe damage to one or both engines, leading to surge,
vibration, and complete thrust loss. The formation of ice can occur
on wing surfaces during exposure of the airplane to normal icing
conditions. Clear ice can also occur on the wing upper surfaces when
cold-soaked fuel is in the main wing fuel tanks, and the airplane is
exposed to conditions of high humidity, rain, drizzle, or fog at
ambient temperatures well above freezing. Often, the ice
accumulation is clear and difficult to detect visually. The ice
forms most frequently on the inboard, aft corner of the main wing
tanks. [End of Cautionary Note].
The wing upper surfaces must be physically checked for ice when the
airplane has been exposed to conditions conducive to ice formation.
Takeoff may not be initiated unless the flight crew verifies that a
visual check and a physical (hands-on) check of the wing upper
surfaces have been accomplished, and that the wing is clear of ice
accumulation when any of the following conditions occur:
(1) When the ambient temperature is less than 50 degrees F and high
humidity or visible moisture (rain, drizzle, sleet, snow, fog, etc.)
is present;
(2) When frost or ice is present on the lower surface of either
wing;
(3) After completion of de-icing.
When inspection aids (i.e. tufts, decals, mount pads, painted
symbols, and paint stripes) are installed in accordance with
McDonnell Douglas MD-80 Service Bulletin 30-59, the physical check
may be made by assuring that all installed tufts move freely.
Note: This limitation does not relieve the requirement that
aircraft surfaces are free of frost, snow, and ice accumulation, as
required by Federal Aviation Regulations Sections 91.527 and
121.629. [End of Note]''
AFM Configuration Deviation List Revision
(3) Within 72 hours after the effective date of this AD, revise
the CDL Appendix of the FAA-approved AFM to include the following
(this may be accomplished by inserting a copy of this AD in the
AFM):
``30-80-01 Triangular Decal and Tuft Assemblies
Up to two (2) decals or tufts per side may be missing, provided:
(a) At least one decal and tuft on each side is located along
the aft spar line; and
(b) The tufts are used for performing the physical check to
determine that the upper wing is free of ice by observing that the
tufts move freely.
Up to eight (8) decals and/or tufts may be missing, provided:
(a) Takeoff may not be initiated unless the flight crew verifies
that a physical (hands-on) check is made of the upper wing in the
location of the missing decals and/or tufts to assure that there is
no ice on the wing when icing conditions exist;
or
(b) When the ambient temperature is more than 50 degrees F.''
Installation of Inspection Aids
(4) Within 30 days after the effective date of this AD, install
inspection aids (i.e., tufts, decals, mount pads, painted symbols,
and paint stripes) on the inboard side of the wings' upper surfaces,
in accordance with McDonnell Douglas Service Bulletin 30-59, dated
September 18, 1989; Revision 1, dated January 5, 1990; or Revision
2, dated August 15, 1990.
Note 8: Operators should note that certain AMOCs have been
approved as acceptable methods of compliance with paragraph (i)(4)
of this AD. Information concerning such AMOCs may be obtained from
the Manager, Los Angeles ACO.
Installation of Overwing Heater Blanket or Primary Upper Wing Ice
Detection System
(j) For airplanes equipped with disabled Honeywell Anti-Ice
Systems installed per STC SA6061NM: Within 3 years after May 7,
2001, accomplish the requirements of paragraph (j)(1), (j)(2), or
(j)(3) of this AD.
(1) Install an overwing heater blanket system, and install an
EPD that provides a circuit-protection function to the overwing
heater blanket, in accordance with a method approved by the Manager,
Los Angeles ACO, FAA.
Note 9: Installation of an overwing heater blanket system and
installation of an EPD that provides a circuit-protection function
to the overwing heater blanket, in accordance with TDG Aerospace,
Inc., SA6042NM, or TDG Master Drawing List (MDL) E93-104, Revision
R, dated October 25, 2000; is an approved means of compliance with
the requirements of paragraph (j)(1) of this AD.
(2) Install an overwing heater blanket system in accordance with
a method approved by the Manager, Los Angeles ACO.
(3) Install an FAA-approved primary upper wing ice detection
system in accordance with a method approved by the Manager, Los
Angeles ACO.
Note 10: Boeing (McDonnell Douglas) has received FAA approval of
an acceptable primary upper wing ice detection system, which is
considered to be an acceptable method of compliance with the
requirements of paragraph (j)(3) of this AD when accomplished in
accordance with a method approved by the Manager, Los Angeles ACO.
AFM Revision
(k)(1) For airplanes equipped with a disabled Honeywell Anti-Ice
Systems installed per STC SA6061NM: Prior to further flight after
accomplishment of the installation required by paragraph (j)(1),
[[Page 12806]]
(j)(2), or (j)(3) of this AD, revise the Limitations Section of the
FAA-approved AFM to include the following (this may be accomplished
by inserting a copy of this AD in the AFM):
``Ice on Wing Upper Surfaces
Caution
Ice shedding from the wing upper surface during takeoff can
cause severe damage to one or both engines, leading to surge,
vibration, and complete thrust loss. The formation of ice can occur
on wing surfaces during exposure of the airplane to normal icing
conditions. Clear ice can also occur on the wing upper surfaces when
cold-soaked fuel is in the main wing fuel tanks, and the airplane is
exposed to conditions of high humidity, rain, drizzle, or fog at
ambient temperatures well above freezing. Often, the ice
accumulation is clear and difficult to detect visually. The ice
forms most frequently on the inboard, aft corner of the main wing
tanks. [End of Cautionary Note]''.
(2) After accomplishment of the installation required by
paragraph (j)(1) of this AD and this AFM revision, the AFM revisions
and CDLs required by paragraphs (i)(2) and (i)(3) of this AD may be
removed from the AFM, and the inspection aids required by paragraph
(i)(4) of this AD may be removed from the airplane.
Alternative Methods of Compliance (AMOCs)
(l)(1) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Los Angeles ACO, FAA. Operators
shall submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Los Angeles ACO.
(2) The following AMOCs were approved previously per AD 92-03-
02, amendment 39-8156, and are approved as AMOCs with the indicated
paragraphs of this AD:
(i) Installation of a non-skid, striped triangular symbol per
Option 5 of McDonnell Douglas Service Bulletin MD80-30-059, Revision
4 though Revision 7, is approved as an AMOC with paragraphs (c) and
(i)(4) of this AD; and
(ii) Revision of the Configuration Deviation List (CDL) Appendix
of the AFM by inserting a copy of CDL Appendix, Section I, Page 2A,
dated March 10, 1993, into the AFM, is approved as an AMOC with
paragraphs (b) and (i)(3) of this AD.
Note 11: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Los Angeles ACO.
Special Flight Permits
(m) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be accomplished.
Incorporation by Reference
(n) Unless otherwise specified in this AD, the actions shall be
done in accordance with the applicable service document identified
in the following table:
------------------------------------------------------------------------
Service document Revision level Date
------------------------------------------------------------------------
Honeywell Alert Service Bulletin Original.......... August 8, 2002
109XXXX-30-38.
McDonnell Douglas Alert Service Original.......... September 22, 1997
Bulletin MD80-30A087.
McDonnell Douglas Service Original.......... September 18, 1989
Bulletin 30-59.
McDonnell Douglas Service 1................. January 5, 1990
Bulletin 30-59.
McDonnell Douglas Service 2................. August 15, 1990
Bulletin 30-59.
McDonnell Douglas Service 02................ February 6, 1996
Bulletin MD80-30-071.
McDonnell Douglas Service 01................ April 8, 1997
Bulletin MD80-30-078.
McDonnell Douglas Service Original.......... October 19, 1999
Bulletin MD80-30-090.
------------------------------------------------------------------------
(1) The incorporation by reference of Honeywell Alert Service
Bulletin 109XXXX-30-38, dated August 8, 2002, was approved
previously by the Director of the Federal Register as of November 8,
2002 (67 FR 65298, October 24, 2002).
(2) The incorporation by reference of McDonnell Douglas Service
Bulletin 30-59, dated September 18, 1989; McDonnell Douglas Service
Bulletin 30-59, Revision 1, dated January 5, 1990; and McDonnell
Douglas Service Bulletin 30-59, Revision 2, dated August 15, 1990;
was approved previously by the Director of the Federal Register as
of January 17, 1992 (57 FR 2014, January 17, 1992).
(3) The incorporation by reference of the remaining service
bulletins listed in Table 1 of this AD, was approved previously by
the Director of the Federal Register as of May 7, 2001 (66 FR 17499,
April 2, 2001).
(4) Copies may be obtained from Boeing Commercial Aircraft
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or
at the FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, California; or at the Office of the
Federal Register, 800 North Capitol Street, NW., Suite 700,
Washington, DC.
Effective Date
(o) The effective date of this amendment remains November 8,
2002.
Issued in Renton, Washington, on March 11, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-6257 Filed 3-17-03; 8:45 am]
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