[Federal Register: September 22, 2005 (Volume 70, Number 183)]
[Proposed Rules]
[Page 55598-55601]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22se05-20]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 55598]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22503; Directorate Identifier 2005-NM-062-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40,
DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain McDonnell Douglas transport category airplanes. This
proposed AD would require an initial ultrasonic inspection for cracks
of the studbolts of the inboard and outboard hinge fittings of the left
and right outboard flaps of the wings. Based on the inspection results,
this proposed AD would also require doing repetitive ultrasonic
inspections, replacing upper and/or lower studbolts with new or
serviceable studbolts, doing a detailed inspection for corrosion of the
upper studbolts, doing a magnetic particle inspection for cracks of
studbolts, and changing the protection treatment; as applicable. This
proposed AD is prompted by reports of corrosion and failures of the
upper and lower studbolts of the outboard flaps inboard and outboard
hinge fittings. We are proposing this AD to prevent corrosion and
subsequent cracking of studbolts, which could result in failure of the
flap hinge fittings and their possible separation from the wing rear
spar, and consequent reduced controllability of the airplane.
DATES: We must receive comments on this proposed AD by November 7,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
By fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood
Boulevard, Long Beach, California 90846, Attention: Data and Service
Management, Dept. C1-L5A (D800-0024).
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401,
on the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-22503; the directorate identifier for this docket is
2005-NM-062-AD.
FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
California 90712-4137; telephone (562) 627-5238; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-22503;
Directorate Identifier 2005-NM-062-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit http://dms.dot.gov.
Examining the Docket
You can examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
We have received several reports of corrosion and failures of the
upper and lower studbolts of the outboard flaps inboard and outboard
hinge fittings on certain McDonnell Douglas Model DC-10-10, DC-10-10F,
DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F,
MD-10-10F, and MD-10-30F airplanes. We have also received several
reports of corrosion of the upper studbolts of the outboard flaps
inboard and outboard hinge fittings on certain McDonnell Douglas Model
MD-11 and -11F airplanes. (The lower studbolts installed on Model MD-11
and -11F airplanes during production are made of corrosion-resistant
material and are not subject to the identified unsafe condition.)
Investigation has shown that the failures are caused by stress
corrosion starting at corrosion pits. Corrosion and subsequent cracking
of the studbolts, if
[[Page 55599]]
not detected and corrected, could result in failure and possible
separation of the flap hinge fittings from the wing rear spar, and
consequent reduced controllability of the airplane.
Relevant Service Information
We have reviewed the service bulletins in the following table:
Referenced Service Bulletins
------------------------------------------------------------------------
Model-- Boeing service bulletin--
------------------------------------------------------------------------
DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC10-57-154, dated February
DC-10-30F (KC-10A and KDC-10), DC-10-40, 2, 2005.
DC-10-40F, MD-10-10F and MD-10-30F
airplanes.
MD-11 and MD-11F airplanes................ MD11-57-076, dated February
2, 2005.
------------------------------------------------------------------------
The service bulletins describe procedures for an initial ultrasonic
inspection for cracks of the upper and lower studbolts (upper only for
MD-11 and -11F airplanes) of the inboard and outboard hinge fittings of
the left and right outboard flaps of the wings. Based on the inspection
results, the service bulletins describe the procedures in the following
two tables:
Condition 1.--(No Cracked Studbolts)
------------------------------------------------------------------------
Option Description
------------------------------------------------------------------------
1......................... Repetitive ultrasonic inspections (described
previously).
2......................... Replacement of the upper and lower studbolts
(as applicable) with new or serviceable
studbolts. Replacing studbolts with
studbolts that have increased corrosion
protection ends the repetitive inspections.
3......................... Removal of upper and lower studbolts (as
applicable), a visual inspection for
corrosion of the studbolts, a magnetic
particle inspection for cracks of studbolts
if necessary, contact Boeing for protection
treatment procedures if necessary, and
installation of new or serviceable
studbolts.
------------------------------------------------------------------------
Condition 2.--(Cracked Studbolts)
------------------------------------------------------------------------
Option Description
------------------------------------------------------------------------
1......................... Removal of upper and lower studbolts (as
applicable), a visual inspection for
corrosion of studbolts, a magnetic particle
inspection for cracks of studbolts if
necessary, installation of new or
serviceable studbolts, and repetitive
ultrasonic inspections (described
previously) if necessary. Replacing
studbolts with studbolts that have
increased corrosion protection ends the
repetitive inspections.
2......................... Replacement of the upper and lower studbolts
(as applicable) with new or serviceable
studbolts.
3......................... Removal of upper and lower studbolts (as
applicable), a detailed inspection for
corrosion of the studbolts, a magnetic
particle inspection for cracks of studbolts
if necessary, and installation of new or
serviceable studbolts.
------------------------------------------------------------------------
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require accomplishing the actions specified in the service
information described previously, except as discussed under
``Differences Between the Proposed AD and Service Bulletins.''
Differences Between the Proposed AD and Service Bulletins
Although the service bulletins specify that operators may contact
the manufacturer for disposition of certain repair conditions, this
proposed AD would require operators to repair those conditions
according to a method approved by the FAA.
The service bulletins refer only to a ``visual inspection'' for
corrosion of studbolts. We have determined that the procedures in the
service bulletins should be described as a ``detailed inspection.''
Note 1 has been included in this proposed AD to define this type of
inspection.
Costs of Compliance
There are about 594 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 297 U.S.-
registered Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F
(KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F
airplanes; and 69 Model MD-11 and -11F airplanes.
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Average Number of U.S.-
Action Work labor rate Parts Cost per registered Fleet cost
hours per hour airplane airplanes
----------------------------------------------------------------------------------------------------------------
Initial ultrasonic inspection 16 $65 None.... $1,040 366 $380,640
----------------------------------------------------------------------------------------------------------------
[[Page 55600]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
McDonnell Douglas: Docket No. FAA-2005-22503; Directorate Identifier
2005-NM-062-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by November 7, 2005.
Affected ADs
(b) None.
Applicability: (c) This AD applies to McDonnell Douglas
airplanes identified in Table 1 of this AD, certificated in any
category.
Table 1.--Applicability
------------------------------------------------------------------------
Model-- As identified in--
------------------------------------------------------------------------
(1) DC-10-10, DC-10-10F, DC-10-15, DC-10- Boeing Service Bulletin
30, DC-10-30F (KC-10A and KDC-10), DC-10- DC10-57-154, dated
40, DC-10-40F, MD-10-10F and MD-10-30F February 2, 2005
airplanes.
(2) MD-11 and MD-11F airplanes............. Boeing Service Bulletin
MD11-57-076, dated
February 2, 2005
------------------------------------------------------------------------
Unsafe Condition
(d) This AD was prompted by reports of corrosion and failures of
the upper and lower studbolts of the outboard flaps inboard and
outboard hinge fittings. We are issuing this AD to prevent corrosion
and subsequent cracking of studbolts, which could result in failure
of the flap hinge fittings and their possible separation from the
wing rear spar, and consequent reduced controllability of the
airplane.
Compliance: (e) You are responsible for having the actions
required by this AD performed within the compliance times specified,
unless the actions have already been done.
Service Bulletins
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the applicable service bulletin
listed in Table 1 of this AD.
Ultrasonic Inspection
(g) Do an ultrasonic inspection for cracks of the upper and
lower studbolts (upper studbolts only for Model MD-11 and -11F
airplanes) of the inboard and outboard hinge fittings of the left
and right outboard flaps of the wings, in accordance with the
service bulletin. Inspect within 72 months from the time the
studbolts were last replaced, or within 24 months after the
effective date of this AD, whichever occurs later.
Condition 1: No Cracked Studbolts
(h) If no cracked upper or lower studbolt is detected during any
ultrasonic inspection required by paragraph (g) of this AD, do the
actions specified in paragraph (i), (j), or (k) of this AD.
Condition 1, Option 1: Repetitive Inspections
(i) Repeat the ultrasonic inspection required by paragraph (g)
of this AD thereafter at intervals not to exceed 24 months, until
the action in paragraph (j)(1), (j)(2), (k)(1), or (k)(2)(i) of this
AD is done.
Condition 1, Option 2: Replacement
(j) Within 72 months from the time the studbolts were last
replaced, or within 24 months after the effective date of this AD,
whichever occurs later, do any one of the replacements in Table 2 of
this AD. Thereafter, at the times specified in Table 2, repeat the
ultrasonic inspection required by paragraph (g) of this AD (if
applicable).
Table 2.--Replacement Parts
------------------------------------------------------------------------
And repeat the
ultrasonic
Replace the upper and lower inspection Accomplishing this
studbolts (as applicable) of the required by replacement
inboard and outboard hinge paragraph (g) of terminates--
fitting with-- this AD
thereafter--
------------------------------------------------------------------------
(1) New studbolts that have None.............. The repetitive
increased corrosion protection inspection
in accordance with the service requirements of
bulletin. paragraph (i),
(j)(3), and
(j)(4) of this
AD.
[[Page 55601]]
(2) Studbolts changed with None.............. The repetitive
protective treatment in inspection
accordance with a method requirements of
approved by the Manager, Los paragraph (i),
Angeles Aircraft Certification (j)(3), and
(ACO), FAA. (j)(4) of this
AD.
(3) Equivalent studbolts in At intervals not None.
accordance with the service to exceed 24
bulletin. months.
(4) Kept serviceable studbolts At intervals not None.
wet with sealant. to exceed 24
months.
------------------------------------------------------------------------
Condition 1, Option 3: Removal, Inspection(s), and Corrective Actions
(k) Within 72 months from the time the studbolts were last
replaced, or within 24 months after the effective date of this AD,
whichever occurs later, remove the upper and lower studbolts (as
applicable) of the inboard and outboard hinge fittings, and do a
detailed inspection for corrosion of the upper and lower studbolts
(as applicable), in accordance with the service bulletin.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(1) If no corroded studbolt is found, before further flight,
change the protective treatment of all upper and lower studbolts (as
applicable) to give increased corrosion protection in accordance
with a method approved by the Manager, Los Angeles ACO, FAA.
Accomplishing this change ends the repetitive inspection
requirements of paragraph (i) of this AD.
(2) If any corroded studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, thereafter do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD, and do a magnetic particle
inspection for cracks in any remaining studbolt in accordance with
the service bulletin.
(i) If no cracked studbolt is found, before further flight,
change the protective treatment of all remaining studbolts to give
increased corrosion protection in accordance with a method approved
by the Manager, Los Angeles ACO, FAA. Accomplishing this change ends
the repetitive inspection requirements of paragraph (i) of this AD.
(ii) If any cracked studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, and thereafter do the repetitive inspections (if
applicable) in accordance with Table 2 of this AD.
Condition 2: Cracked Studbolts
(l) If any cracked studbolt is detected during any ultrasonic
inspection required by paragraph (g) of this AD, before further
fight, do the actions specified in paragraph (m), (n), or (o) of
this AD.
Condition 2, Option 1: Removal, Inspection(s), and Corrective Actions
(m) Remove any cracked upper and lower studbolt (as applicable)
of the inboard and outboard hinge fittings, install any studbolt
identified in and in accordance with Table 2 of this AD, do the
repetitive inspections (if applicable) in accordance with Table 2 of
this AD, and do a detailed inspection for corrosion of any remaining
studbolts in accordance with the service bulletin.
(1) If no corroded studbolt is found, before further flight, do
a magnetic particle inspection for cracks in any remaining studbolt
in accordance with the service bulletin. If any crack is found,
before further flight, install any studbolt identified in and in
accordance with Table 2 of this AD and do the repetitive inspections
(if applicable) in accordance with Table 2 of this AD.
(2) If any corroded studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, do the repetitive inspections (if applicable) in accordance
with Table 2 of this AD, and do a magnetic particle inspection for
cracks in any remaining studbolt in accordance with the service
bulletin.
(i) If no cracked studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, and do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD.
(ii) If any cracked studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, and do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD.
Condition 2, Option 2: Replacement
(n) Replace all studbolts in accordance with paragraph (j) of
this AD.
Condition 2, Option 3: Removal, Inspections, and Installation
(o) Remove any cracked studbolt, install any studbolt identified
in and in accordance with Table 2 of this AD, do the repetitive
inspections (if applicable) in accordance with Table 2 of this AD,
and do a detailed inspection for corrosion of any remaining studbolt
in accordance with the service bulletin.
(1) If no corroded studbolt is found, before further flight, do
a magnetic particle inspection for cracks in any remaining studbolt
in accordance with the service bulletin, and change the protective
treatment of all remaining upper and lower studbolts (as applicable)
to give increased corrosion protection in accordance with a method
approved by the Manager, Los Angeles ACO, FAA. Accomplishing this
change ends the repetitive inspection requirements of paragraph (i)
of this AD.
(2) If any corroded studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, do the repetitive inspections (if applicable) in accordance
with Table 2 of this AD, and do a magnetic particle inspection for
cracks in any remaining studbolt in accordance with the service
bulletin.
(i) If no cracked studbolt is found, before further flight,
change the protective treatment of all remaining studbolts to give
increased corrosion protection in accordance with a method approved
by the Manager, Los Angeles ACO, FAA. Accomplishing this change ends
the repetitive inspection requirements of paragraph (i) of this AD.
(ii) If any cracked studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, and do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD.
Alternative Methods of Compliance (AMOCs)
(p) The Manager, Los Angeles ACO, FAA, has the authority to
approve AMOCs for this AD, if requested in accordance with the
procedures found in 14 CFR 39.19.
Issued in Renton, Washington, on September 15, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-18907 Filed 9-21-05; 8:45 am]
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