FR Doc 06-8227

[Federal Register: September 28, 2006 (Volume 71, Number 188)]
[Rules and Regulations]
[Page 56861-56864]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28se06-5]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24865; Directorate Identifier 2005-NM-194-AD;
Amendment 39-14771; AD 2006-20-02]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747 airplanes. That AD
currently requires inspections to detect disbonding, corrosion, and
cracking at the longitudinal rows of fasteners in the bonded skin
panels in section 41 of the fuselage, and repair, if necessary. This
new AD adds airplanes to the applicability, and requires new
inspections of airplanes that may have Alodine-coated rivets installed.
This AD results from a report of cracking discovered in a skin lap
joint that was previously inspected using the eddy current method. We
are issuing this AD to prevent rapid decompression of the airplane due
to disbonding and subsequent cracking of the skin panels.

DATES: This AD becomes effective November 2, 2006.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 2,
2006.
On November 27, 1996 (61 FR 57994, November 12, 1996), the Director
of the Federal Register approved the incorporation by reference of
Boeing Alert Service Bulletin 747-53A2409, dated September 26, 1996.

ADDRESSES: You may examine the 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., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437;
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 96-23-02, amendment 39-
9807 (61 FR 57994, November 12, 1996). The existing AD applies to
certain Boeing Model 747 series airplanes. That NPRM was published in
the Federal Register on May 25, 2006 (71 FR 30090). That NPRM proposed
to continue to require inspections to detect disbonding, corrosion, and
cracking at the longitudinal rows of fasteners in the bonded skin
panels in section 41 of the fuselage, and repair, if necessary. That
NPRM also proposed to add airplanes to the applicability of the
existing AD, and require new inspections of airplanes that may have
Alodine-coated rivets installed.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.

Support for the NPRM

Boeing supports the NPRM.

[[Page 56862]]

Request To Clarify Inspection Applicability in Paragraph (g)(1) of the
NPRM

Northwest Airlines (NWA) requests that we use ``and/or'' in place
of ``and'' in paragraph (g)(1) of the NPRM, as follows: ``* * * do
initial inspections of Area 4 and repetitive inspections, as
applicable, to detect disbonding, corrosion, and/or cracking of the
skin; * * *.'' NWA explains that changing ``and'' to ``and/or''
provides clear instruction for accomplishing the inspection of Area 4
using one of the inspection methods defined in Figure 18 or 20 of
Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August 18,
2005, which was referenced in the NPRM as the appropriate source of
service information for accomplishing the required actions. NWA states
that the requested change eliminates all possibility of interpreting
the NPRM to require a specific inspection for disbonding, corrosion,
and cracking using the applicable method for each inspection as defined
in the service bulletin. NWA also states that this change would
duplicate the inspection methods specified in paragraphs (b), (h), and
(n) of AD 96-23-02, which used the words ``and/or'' in a similar
context. This change would ensure the NPRM provides clear definition
that an operator would accomplish one inspection using the applicable
method to detect disbonding, corrosion, or cracks, rather than
accomplishing three inspections for three specific and separate
conditions.
We agree that the paragraph should be clarified to provide clear
instruction for accomplishing the inspection of Area 4 using one of the
inspection methods defined in the service bulletin. We disagree with
using the words ``and/or.'' Our recent policy has been to avoid using
and/or, which can often be subject to misinterpretation. Therefore, we
have changed paragraph (g)(1) of this AD by adding ``as applicable'' at
the end of the phrase as follows: ``* * * do initial inspections of
Area 4 and repetitive inspections, as applicable, to detect disbonding,
corrosion, and cracking of the skin, as applicable; * * * .''

Request To Clarify Inspection Methods in Paragraph (g)(1) of the NPRM

NWA also requests that we change the inspection methods in
paragraph (g)(1) of the NPRM from ``Method 1 or 2'' to ``Method 2, 3,
or 4'' as follows: ``If inspection Method 2, 3, or 4 is used and no
disbonded doubler is found, no further action is required by this AD.''
NWA explains that changing the inspection methods from ``Method 1 or
2'' to ``Method 2, 3, or 4'' would define the inspection methods
necessary to inspect the fuselage skins. Inspection Method 1 is an
external ultrasonic inspection that is not applicable to Area 4.
Inspection Methods 2, 3, and 4 are inspections that apply to Area 4 and
are defined in Figure 20 of the service bulletin.
We partially agree. We agree that inspection Method 1 does not
belong in the paragraph because the Method 1 inspection is applicable
only to areas 1, 2, and 3. We disagree with including Methods 3 and 4
in a statement that contains the words, ``no further action is required
by this AD.'' Inspection Methods 3 and 4 are repetitive inspections. If
we included these inspection methods in this statement, then the
repetitive inspections would no longer be required. Therefore, we have
changed the specified part of paragraph (g)(1) of the final rule as
follows: ``If inspection Method 2 is used and no disbonded doubler is
found, no further action is required by this AD.'' Furthermore, we
eliminated all other references to Method 1 from the paragraph.

Conclusion

We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

There are about 623 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD. The average labor rate is $80
per work hour.

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
airplane, per U.S.- Fleet cost, per inspection
Action Work hours inspection registered cycle
cycle airplanes
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Inspections (required by AD 96-23- 308 $24,640 79 $1,946,560.
02, and continued in this AD).
New inspections (for airplanes 42 3,360 96 Up to $322,560.
with Alodine-coated rivets).
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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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under 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 AD and placed it in the AD docket.

[[Page 56863]]

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, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-9807 (61 FR 57994, November 12, 1996) and by
adding the following new airworthiness directive (AD):

2006-20-02 Boeing: Amendment 39-14771. Docket No. FAA-2006-24865;
Directorate Identifier 2005-NM-194-AD.

Effective Date

(a) This AD becomes effective November 2, 2006.

Affected ADs

(b) This AD supersedes AD 96-23-02.

Applicability

(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-
400F, 747SR, and 747SP series airplanes, certificated in any
category; as identified in Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005.

Unsafe Condition

(d) This AD results from a report of cracking discovered in a
skin lap joint that was previously inspected using the eddy current
method. We are issuing this AD to prevent rapid decompression of the
airplane due to disbonding and subsequent cracking of the skin
panels.

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.

Requirements of AD 96-23-02

Actions for Groups 1 Through 10, and 17 Through 36, as Specified in
Boeing Alert Service Bulletin 747-53A2409, Revision 5

(f) For airplanes identified as Groups 1 through 10 inclusive,
and 17 through 36 inclusive, in Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005: Do the inspections in
paragraph (f)(1) of this AD; and do the corrective action in
paragraph (f)(2) of this AD as applicable. Except as provided by
paragraph (i) of this AD, do all actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2409, dated September 26, 1996; or Revision 5, dated August 18,
2005. After the effective date of this AD, only Revision 5 of the
service bulletin may be used.
(1) At the applicable time in Figures 1, 2, 18, and 20 of
Revision 5 of the service bulletin, do initial and repetitive
inspections of Areas 1 and 4, as applicable, to detect disbonding,
corrosion, and cracking of the skin; except any inspection using
Method 1 or 2 must not be accomplished before the latest of the
following, as applicable: Before the accumulation of 2,000 total
flight cycles; 2,000 flight cycles since modification to the
stretched upper deck (SUD) configuration; or 2,000 flight cycles
since skin panel replacement in accordance with AD 90-26-10,
amendment 39-6836. If inspection Method 1 or 2 is used and no
disbonded doubler is found, no further action is required by this
AD.
(2) If any corrosion or cracking is found during any inspection
required by paragraph (f)(1) of this AD: Before further flight,
except as provided by paragraph (i) of this AD, repair and do any
applicable related investigative actions in accordance with the
Accomplishment Instructions of Revision 5 of the service bulletin.

New Requirements of This AD

Actions for Groups 11 Through 16 as Specified in Boeing Alert
Service Bulletin 747-53A2409, Revision 5 (Airplanes Added to the
Applicability of This AD)

(g) For airplanes identified as Groups 11 through 16 inclusive
in Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated
August 18, 2005: Do the inspections in paragraph (g)(1) of this AD;
and do the corrective action in paragraph (g)(2) of this AD as
applicable. Except as provided by paragraph (i) of this AD, do all
actions in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2409, Revision 5, dated August 18,
2005.
(1) At the applicable time in Figures 18 and 20 of the service
bulletin, do initial inspections of Area 4 and repetitive
inspections, as applicable, to detect disbonding, corrosion, and
cracking of the skin, as applicable; except any inspection using
Method 2 must not be accomplished before the latest of the
following, as applicable: Before the accumulation of 2,000 total
flight cycles; 2,000 flight cycles since modification to the SUD
configuration; or 2,000 flight cycles since skin panel replacement
in accordance with AD 90-26-10. If inspection Method 2 is used and
no disbonded doubler is found, no further action is required by this
AD.
(2) If any corrosion, disbonding, or cracking is found during
any inspection required by paragraph (g)(1) of this AD, before
further flight: Repair and do any applicable related investigative
actions in accordance with the Accomplishment Instructions of the
service bulletin.

Actions for Airplanes With Alodine-Coated Rivets for Groups 1
Through 10, and 17 Through 36 as Specified in Boeing Alert Service
Bulletin 747-53A2409, Revision 5

(h) For airplanes identified as Groups 1 through 10 inclusive,
and 17 through 36 inclusive, in Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005: Do the inspections in
paragraph (h)(1) of this AD; and do the corrective action in
paragraph (h)(2) of this AD if necessary. Except as provided by
paragraph (i) of this AD, do all actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005.
(1) At the applicable time in Figures 21 and 22 of the service
bulletin: Do initial and repetitive inspections of Areas 1 and 4, as
applicable, to detect cracking of the skin.
(2) If any cracking is found during any inspection required by
paragraph (h)(1) of this AD, before further flight: Repair in
accordance with the Accomplishment Instructions of the service
bulletin.

Exceptions

(i) Do all actions in accordance with the applicable service
bulletin except as provided by paragraphs (i)(1), (i)(2), (i)(3),
(i)(4), and (i)(5) of this AD.
(1) For the action in paragraph (f)(1) of this AD: Where Boeing
Alert Service Bulletin 747-53A2409, dated September 26, 1996; and
Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated August
18, 2005; specify a compliance time after the issuance of any
revision of the service bulletin, this paragraph requires compliance
before the specified compliance time after November 27, 1996 (the
effective date of AD 96-23-02).
(2) For the actions in paragraphs (g)(1) and (h)(1) of this AD:
Where Boeing Alert Service Bulletin 747-53A2409, Revision 5, dated
August 18, 2005, specifies a compliance time after the issuance or
receipt of any revision of the service bulletin, this paragraph
requires compliance before the specified compliance time after the
effective date of this AD.
(3) For any repair or any inspection where Boeing Alert Service
Bulletin 747-53A2409, Revision 5, dated August 18, 2005, specifies
to contact the manufacturer for further instructions: Before further
flight, repair or inspect using a method approved in accordance with
the procedures specified in paragraph (k) of this AD.
(4) If corrosion is found during any inspection required by this
AD, before further flight: Repair in accordance with an FAA-approved
method.
(5) Where Boeing Alert Service Bulletin 747-53A2409, Revision 5,
dated August 18, 2005, specifies that it is not necessary to count
flight cycles at 2.0 psi or less cabin differential pressure, this
AD does not allow for that adjustment factor.

Credit for Actions Accomplished Previously

(j) Actions done before the effective date of this AD in
accordance with the service bulletins specified in Table 1 of this
AD are acceptable for compliance with the corresponding requirements
of paragraphs (f) and (g) of this AD.

[[Page 56864]]

Table 1.--Credit Service Bulletins
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Revision
Service bulletin level Date
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Boeing Service Bulletin 747- 1 May 29, 1997.
53A2409.
Boeing Service Bulletin 747- 2 August 6, 1998.
53A2409.
Boeing Service Bulletin 747- 3 October 22, 1998.
53A2409.
Boeing Service Bulletin 747- 4 February 17, 2000.
53A2409.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 96-23-02,
are approved as AMOCs for the corresponding provisions of paragraph
(f) of this AD, except AMOCs for terminating action based upon
inspection results using a sliding probe low frequency eddy current
(LFEC), sliding probe high frequency eddy current (HFEC), or mid
frequency surface eddy current (MFEC) inspection methods; and
provided that any alternative method for future inspections did not
incorporate a sliding probe LFEC, sliding probe HFEC, or MFEC
inspection methods.
(4) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane and the approval must specifically refer to this AD.

Material Incorporated by Reference

(l) You must use Boeing Alert Service Bulletin 747-53A2409,
dated September 26, 1996; or Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005, as applicable, to
perform the actions that are required by this AD, unless the AD
specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2409, Revision 5, dated August 18, 2005, in accordance with 5
U.S.C. 552(a) and 1 CFR part 51.
(2) On November 27, 1996 (61 FR 57994, November 12, 1996), the
Director of the Federal Register approved the incorporation by
reference of Boeing Alert Service Bulletin 747-53A2409, dated
September 26, 1996.
(3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at http://dms.dot.gov; or

at the National Archives and Records Administration (NARA). For
information on the availability of this material at the NARA, call
(202) 741-6030, or go to http://www.archives.gov/[fxsp0]federal--

Issued in Renton, Washington, on September 14, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-8227 Filed 9-27-06; 8:45 am]

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