Airworthiness Directives; The Boeing Company Airplanes

[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)]
[Rules and Regulations]
[Pages 14707-14711]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-06001]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0774; Directorate Identifier 2013-NM-154-AD; 
Amendment 39-18438; AD 2016-06-07]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2006-22-15 for 
all The Boeing Company 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. AD 2006-22-15 required repetitive inspections 
for cracking of certain panel webs and stiffeners of the nose wheel 
well (NWW), and corrective actions if necessary; and replacement of 
certain panels with new panels, which terminates the repetitive 
inspections. This new AD reduces a compliance time and adds certain 
inspections and an applicable repair. This AD was prompted by multiple 
reports of fatigue cracking in the NWW top panel and side panel webs 
and stiffeners. We are issuing this AD to prevent fatigue cracking of 
the NWW side and top panels, which could result in a NWW 
depressurization event severe enough to reduce the structural integrity 
of the fuselage.

DATES: This AD is effective April 22, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 22, 
2016.

ADDRESSES: For service information identified in this final rule, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, WA. For information on the availability of this material at the 
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0774.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0774; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6432; fax: 425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2006-22-15, Amendment 39-14812 (71 
FR 64884, November 6, 2006) (``AD 2006-22-15''). AD 2006-22-15 applied 
to all The Boeing Company 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. The SNPRM published in the Federal Register 
on September 18, 2015 (80 FR 56407) (``the SNPRM''). We preceded the 
SNPRM with a notice of proposed rulemaking (NPRM) that published in the 
Federal Register on November 17, 2014 (79 FR 68388) (``the NPRM''). The 
NPRM proposed to continue to require repetitive inspections for 
cracking of

[[Page 14708]]

certain panel webs and stiffeners of the NWW, and corrective actions if 
necessary; and replacement of certain panels with new panels, which 
terminates the repetitive inspections. The NPRM proposed to reduce a 
compliance time and add certain inspections and repair if necessary. 
The NPRM was prompted by reports of fatigue cracking in the panel webs 
and stiffeners of the NWW found prior to the inspection threshold of AD 
2006-22-15. The SNPRM revised the NPRM by specifying a repetitive 
inspection interval for a certain NWW area inspection. We are issuing 
this AD to prevent fatigue cracking of the NWW side and top panels, 
which could result in a NWW depressurization event severe enough to 
reduce the structural integrity of the fuselage.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the SNPRM and 
the FAA's response to each comment.

Support for the SNPRM

    Two commenters supported the SNPRM. One commenter stated that the 
FAA should continue to execute its administrative power to ensure 
traveler safety and industry compliance, adding that while the original 
rule was good, ensuring that specifics are covered and timetables are 
available is an important improvement.

Request for Credit for Compliance Times in Previously Approved 
Alternative Methods of Compliance (AMOCs)

    Boeing requested that we allow credit for the compliance times in 
previously approved AMOCs, if the compliance times are acceptable 
according to the SNPRM.
    We agree with the commenter's request. We have revised paragraph 
(p)(4) of this AD to state that: AMOC actions approved previously for 
AD 2006-22-15 are approved as AMOCs for the corresponding actions of 
this AD. In addition, paragraph (p)(4) of this AD states that the 
compliance times in AMOCs approved previously for AD 2006-22-15 are not 
approved for the corresponding actions and compliance times in this AD, 
if this AD specifies an earlier compliance time than that specified in 
AD 2006-22-15; and that compliance times in AMOCs approved previously 
for AD 2006-22-15 that meet the requirements of this AD are acceptable.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the change described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the SNPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed the following Boeing service bulletins.
    <bullet> Boeing Alert Service Bulletin 747-53A2808, dated November 
30, 2012. This service information describes procedures for replacement 
of the side and top panel webs, support beams, and stiffeners of the 
NWW; an inspection for cracking of the attaching structural elements 
that are common to the removed top and side panels of the NWW; 
repetitive post-modification inspections for cracks in the top and side 
panel webs and stiffeners; and repairs.
    <bullet> Boeing Service Bulletin 747-53A2465, Revision 5, dated 
July 11, 2013. This service information describes procedures for doing 
inspections for cracking of the NWW side panel and top panel webs and 
longitudinal stiffeners for cracks, and related investigative and 
corrective actions.
    <bullet> Boeing Service Bulletin 747-53A2562, Revision 3, dated 
July 11, 2013. This service information describes procedures for 
replacement of the side and top panel webs and certain stiffeners of 
the NWW; an inspection for cracks in attaching structural elements that 
are common to the removed top panel and side panels; repetitive post-
modification inspections for cracks in the top and side panel webs and 
stiffeners; and repairs.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD will affect 255 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per  product       operators
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained     119 work-hours x    $0................  $10,115 per         $2,579,325 per
 from AD 2006-22-15].              $85 per hour =                          inspection cycle.   inspection cycle.
                                   $10,115 per
                                   inspection cycle.
Modification [actions retained    Up to 1,346 work-   Up to $144,248....  Up to $258,658....  Up to $65,957,790.
 from AD 2006-22-15].              hours x $85 per
                                   hour = $114,410.
Post-modification Inspections     119 work-hours x    $0................  $10,115 per         $2,579,325 per
 [new action].                     $85 per hour =                          inspection cycle.   inspection cycle.
                                   $10,115 per
                                   inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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

[[Page 14709]]

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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    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 FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006) (``AD 
2006-22-15''), and adding the following new AD:

2016-06-07 The Boeing Company: Amendment 39-18438; Docket No. FAA-
2014-0774; Directorate Identifier 2013-NM-154-AD.

(a) Effective Date

    This AD is effective April 22, 2016.

(b) Affected ADs

    This AD replaces AD 2006-22-15, Amendment 39-14812 (71 FR 64884, 
November 6, 2006) (``AD 2006-22-15'').

(c) Applicability

    This AD applies to all The Boeing Company 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.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by multiple reports of cracking in the nose 
wheel well (NWW) top panel and side panel webs and stiffeners. We 
are issuing this AD to prevent fatigue cracking of the NWW side and 
top panels, which could result in a NWW depressurization event 
severe enough to reduce the structural integrity of the fuselage.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspections and Corrective Actions With New Compliance 
Times

    Except as specified in paragraphs (h)(1) and (h)(2) of this AD, 
at the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 
2013: Do the actions specified in paragraphs (g)(1), (g)(2), and 
(g)(3) of this AD, and do all applicable related investigative and 
corrective actions; in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2465, Revision 5, 
dated July 11, 2013, except as specified in paragraph (h)(3) of this 
AD. Do all applicable related investigative and corrective actions 
before further flight. Repeat the inspections specified in 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD thereafter at the 
applicable intervals specified in paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 
2013. The repetitive interval for the inspection of Area 2 specified 
in table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, is 1,000 
flight cycles. In table 2 and table 3 in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5, 
dated July 11, 2013, the date ``January 27, 2005,'' is the effective 
date of AD 2004-25-23, Amendment 39-13911 (69 FR 76839, December 23, 
2004); and the date ``May 10, 2005,'' is the effective date of AD 
2005-09-02, Amendment 39-14070 (70 FR 21141, April 25, 2005; 
corrected May 25, 2005 (70 FR 29940)).
    (1) Do an external detailed inspection for cracks of the top and 
sidewall panel webs of the NWW (specified as Area 1 and Area 2 in 
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11, 
2013).
    (2) Do internal detailed and surface high frequency eddy current 
(HFEC) inspections for cracks of the sidewall panel and top panel 
stiffeners of the NWW (specified as Area 3 in Boeing Service 
Bulletin 747-53A2465, Revision 5, dated July 11, 2013).
    (3) Do an external detailed and ultrasonic testing (UT) 
inspection for cracks of the top and sidewall panel webs of the NWW 
(specified as Area 1 and Area 2 in Boeing Service Bulletin 747-
53A2465, Revision 5, dated July 11, 2013).

(h) Exceptions to Boeing Service Bulletin 747-53A2465, Revision 5, 
Dated July 11, 2013

    (1) Table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, applies to 
airplanes with less than 15,000 total flight cycles ``as of the 
Revision 5 date of this service bulletin.'' For this AD, however, 
table 1 applies to airplanes with the specified total flight cycles 
as of the effective date of this AD.
    (2) Table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, specifies a 
compliance time of ``13,000 total flight-cycles,'' or ``within 1,000 
flight cycles after the Revision 5 date of this service bulletin,'' 
whichever occurs later. This AD requires compliance before the 
accumulation of 10,000 total flight cycles or within 1,000 flight 
cycles after the effective date of this AD, whichever occurs later.
    (3) If any cracking or damage is found during any inspection 
required by paragraph (g) of this AD, and Boeing Service Bulletin 
747-53A2465, Revision 5, dated July 11, 2013, specifies to contact 
Boeing for appropriate action: Before further flight, repair the 
cracking or damage using a method approved in accordance with the 
procedures specified in paragraph (p) of this AD.

(i) NWW Modification

    For airplanes identified in Boeing Service Bulletin 747-53A2562, 
Revision 3, dated July 11, 2013: At the applicable time specified in 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2562, Revision 3, dated July 11, 2013, replace the left-side, 
right-side, and top panels of the NWW, as applicable, with new 
panels, in accordance with the Accomplishment Instructions of Boeing 
Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. As of 
the effective date of this AD, concurrently with doing the 
replacement specified in Boeing Service Bulletin 747-53A2562, 
Revision 3, dated July 11, 2013, do a detailed inspection for any 
cracks or damage (including, but not limited to, dents and 
corrosion) in all attaching structural elements that are common to 
the removed top panel and side panels, as applicable, and do all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 747-53A2562, Revision 3, 
dated July 11, 2013. If any crack or damage is found, before further 
flight, repair the cracking or damage using a method approved in 
accordance with the procedures specified in paragraph (p) of this 
AD. In paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 
747-53A2562, Revision 3, dated July 11, 2013, the date ``December 
11, 2006,'' is the effective date of AD 2006-22-15.

[[Page 14710]]

(j) Repetitive Post-Modification Inspections

    For airplanes on which the replacement specified in paragraph 
(i) of this AD has been done: Except as required by paragraph (k) of 
this AD, at the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Service Bulletin 747-53A2562, Revision 3, 
dated July 11, 2013, do the actions specified in paragraphs (j)(1), 
(j)(2), and (j)(3) of this AD. If any crack is found: Before further 
flight, repair the cracking using a method approved in accordance 
with the procedures specified in paragraph (p) of this AD. Repeat 
the inspections specified in paragraphs (j)(1), (j)(2), and (j)(3) 
of this AD thereafter at the applicable intervals specified in 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2562, Revision 3, dated July 11, 2013.
    (1) Do an external detailed inspection for cracks in the side 
panel webs, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 
2013.
    (2) Do an internal detailed inspection and high frequency eddy 
current (HFEC) inspection for cracks in the top and side panel 
stiffeners, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 
2013.
    (3) Do an external detailed inspection for cracks in the top 
panel web, in accordance with the Accomplishment Instructions of 
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11, 
2013.

(k) Exception to Boeing Service Bulletin 747-53A2562, Revision 3, Dated 
July 11, 2013

    Where paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 
747-53A2562, Revision 3, dated July 11, 2013, specifies a compliance 
time relative to the ``Revision 3 date of this service bulletin,'' 
this AD requires compliance within the specified compliance time 
after the effective date of this AD.

(l) NWW Modification for Certain Airplanes

    For airplanes identified in Boeing Alert Service Bulletin 747-
53A2808, dated November 30, 2012: At the applicable time specified 
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2808, dated November 30, 2012, replace the left side, right 
side, and top panels of the NWW, as applicable, with new panels, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2808, dated November 30, 2012. Concurrently 
with doing the replacement specified in this paragraph, do a 
detailed inspection for cracks of the attaching structural elements 
that are common to the removed top, left side, and right side panels 
of the NWW, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012. 
If any crack is found, before further flight, repair the cracking 
using a method approved in accordance with the procedures specified 
in paragraph (p) of this AD.

(m) Repetitive Post-Modification Inspections for Certain Airplanes

    For airplanes on which the replacement specified in paragraph 
(l) of this AD has been done: At the applicable time specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
747-53A2808, dated November 30, 2012, do the actions specified in 
paragraphs (m)(1), (m)(2), and (m)(3) of this AD. If any crack is 
found: Before further flight, repair the cracking using a method 
approved in accordance with the procedures specified in paragraph 
(p) of this AD. Repeat the inspections specified in paragraphs 
(m)(1), (m)(2), and (m)(3) of this AD thereafter at the applicable 
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing 
Alert Service Bulletin 747-53A2808, dated November 30, 2012.
    (1) Do an external detailed inspection for cracks in the side 
panel webs, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012.
    (2) Do an internal detailed inspection and HFEC inspection for 
cracks in the top and side panel stiffeners, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2808, dated November 30, 2012.
    (3) Do an external detailed inspection for cracks in the top 
panel web, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012.

(n) Terminating Action for Certain Repetitive Inspections

    Replacing the left side, right side, and top panels of the NWW 
with new panels as specified in paragraph (i) or (l) of this AD 
terminates the repetitive inspections required by paragraph (g) of 
this AD.

(o) Credit for Previous Actions

    (1) This paragraph restates the credit given in paragraph (k) of 
AD 2006-22-15.
    (i) This paragraph provides credit for the actions required by 
paragraph (g)(1) of this AD, if those actions were performed before 
January 27, 2005 (the effective date of AD 2004-25-23, Amendment 39-
13911 (69 FR 76839, December 23, 2004)), using Boeing Alert Service 
Bulletin 747-53A2465, dated April 5, 2001, which is not incorporated 
by reference in this AD.
    (ii) This paragraph provides credit for actions required by 
paragraphs (g)(1) and (g)(2) of this AD, if those actions were 
performed before December 11, 2006 (the effective date of AD 2006-
22-15), using a service bulletin identified in paragraph 
(o)(1)(ii)(A), (o)(1)(ii)(B), or (o)(1)(ii)(C) of this AD, which are 
not incorporated by reference in this AD.
    (A) Boeing Alert Service Bulletin 747-53A2465, Revision 1, dated 
October 16, 2003.
    (B) Boeing Alert Service Bulletin 747-53A2465, Revision 2, dated 
November 11, 2004.
    (C) Boeing Alert Service Bulletin 747-53A2465, Revision 3, dated 
December 23, 2004.
    (2) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2465, Revision 4, dated February 24, 2005, which is not 
incorporated by reference in this AD.
    (3) This paragraph provides credit for the actions required by 
paragraphs (i) and (j) of this AD, if those actions were performed 
before the effective date of this AD using the service information 
identified in paragraph (o)(3)(i) or (o)(3)(ii) of this AD.
    (i) Boeing Service Bulletin 747-53A2562, Revision 1, dated July 
28, 2005, which was incorporated by reference in AD 2006-22-15.
    (ii) Boeing Service Bulletin 747-53A2562, Revision 2, dated May 
31, 2007, which is not incorporated by reference in this AD.

(p) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (q)(1) of this AD. 
Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by the Boeing Commercial Airplanes Organization 
Designation Authorization (ODA) that has been authorized by the 
Manager, Seattle ACO, to make those findings. To be approved, the 
repair method, modification deviation, or alteration deviation must 
meet the certification basis of the airplane, and the approval must 
specifically refer to this AD.
    (4) AMOC actions approved previously for AD 2006-22-15 are 
approved as AMOCs for the corresponding actions of this AD. The 
compliance times in AMOCs approved previously for AD 2006-22-15 are 
not approved for the corresponding actions and compliance times in 
this AD, if this AD specifies an earlier compliance time than that 
specified in AD 2006-22-15. Compliance times in AMOCs approved 
previously for AD 2006-22-15 that meet the requirements of this AD 
are acceptable.

(q) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432; 
fax: 425-917-6590; email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(3) and (r)(4) of this AD.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference

[[Page 14711]]

(IBR) of the service information listed in this paragraph under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Boeing Alert Service Bulletin 747-53A2808, dated November 
30, 2012.
    (ii) Boeing Service Bulletin 747-53A2465, Revision 5, dated July 
11, 2013.
    (iii) Boeing Service Bulletin 747-53A2562, Revision 3, dated 
July 11, 2013.
    (3) For Boeing service information identified in this AD, 
contact Boeing Commercial Airplanes, Attention: Data & Services 
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
https://www.myboeingfleet.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on March 9, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-06001 Filed 3-17-16; 8:45 am]
BILLING CODE 4910-13-P

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