AD 2013-07-07

[Federal Register Volume 78, Number 72 (Monday, April 15, 2013)]
[Rules and Regulations]
[Pages 22182-22185]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2013-08193]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0933; Directorate Identifier 2012-NM-107-AD; 
Amendment 39-17411; AD 2013-07-07]
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 adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER 
series airplanes. This AD was prompted by reports of an incorrect 
procedure used to apply the wear and corrosion protective surface 
coating to attach pins of the horizontal stabilizer rear spar. This AD 
requires inspecting to determine the part number of the attach pins of 
the horizontal stabilizer rear spar, and replacing certain attach pins 
with new, improved attach pins. We are issuing this AD to prevent 
premature failure of the attach pins, which could cause reduced 
structural integrity of the horizontal stabilizer to fuselage 
attachment, resulting in loss of control of the airplane.

DATES: This AD is effective May 20, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 20, 2013.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data

[[Page 22183]]

& Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may review copies of the 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 Document 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: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6440; fax: 
425-917-6590; email <a href="/cdn-cgi/l/email-protection#8ee0efe0edf7a0e3effcfde6cee8efefa0e9e1f8"><span class="__cf_email__" data-cfemail="2b454a45485205464a5958436b4d4a4a054c445d">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM published in the Federal Register on September 12, 2012 (77 
FR 56170). That NPRM proposed to require inspecting to determine the 
part number of the attach pins of the horizontal stabilizer rear spar, 
and replacing certain attach pins with new, improved attach pins.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 56170, September 12, 2012) and the FAA's response to each 
comment.

Concurrence With NPRM (77 FR 56170, September 12, 2012)

    Boeing concurs with the content of the proposed rule (77 FR 56170, 
September 12, 2012).

Request for Alternative Method of Compliance (AMOC) to Inspections 
Required by AD 2004-05-19, Amendment 39-13514 (69 FR 10921, March 9, 
2004; Corrected April 13, 2004 (69 FR 19313))

    Europe Airpost requested that a statement be included in the NPRM 
(77 FR 56170, September 12, 2012) that approves installation of the 
horizontal stabilizer rear spar attachment pins part number (P/N) 
180A1612-7 and 180A1612-8 as an AMOC to the inspections required by AD 
2004-05-19, Amendment 39-13514 (69 FR 10921, March 9, 2004; corrected 
April 13, 2004 (69 FR 19313)) provided that the special inspections 
specified in the Boeing maintenance planning data (MPD) document are 
performed.
    We agree with the request. We have added paragraph (j) to this 
final rule to state that accomplishing the actions required by 
paragraphs (g) and (h) of this AD terminates the requirements of 
paragraphs (a), (b), (c), (d), and (e) of AD 2004-05-19 Amendment 39-
13514 (69 FR 10921, March 9, 2004; corrected April 13, 2004 (69 FR 
19313)), for rear spar attach pins only.

Request for Exclusions

    Delta Air Lines (Delta) requested that we provide exclusions in 
paragraph (g) of the NPRM (77 FR 56170, September 12, 2012) for certain 
airplanes that may not be affected by the discrepant stabilizer pins. 
Delta stated that airplanes that were not delivered between August 1, 
2006, and July 31, 2008, have not had the terminating action 
accomplished according to AD 2004-05-19, Amendment 39-13514 (69 FR 
10921, March 9, 2004; corrected April 13, 2004 (69 FR 19313)), and did 
not have maintenance done in accordance with the MPD, would not need to 
be inspected. Delta also requested that we provide exclusions to 
paragraph (i) of the NPRM because spare pins having P/N 180A1612-3 and 
180A1612-4 delivered by Boeing Spares before June 30, 2006, and after 
June 17, 2008, are not suspected of having unapproved surface coatings.
    We disagree with the request to change paragraphs (g) and (i) in 
this final rule. Although Boeing has specified certain airplane 
delivery dates associated with the discrepant pins, as well as delivery 
dates for pins suspected to be discrepant and distributed as spare 
parts, other factors make identification of the affected airplanes 
difficult. Stabilizers are rotable components, and therefore stabilizer 
attach pins may be different from those delivered with the airplane. To 
assist operators in inspecting for the suspect pins, paragraph (g) of 
this final rule (as proposed in the NPRM (77 FR 56170, September 12, 
2012)) allows for a records search to be used to confirm the part 
number of the rear spar attachment pin, if such a record search is 
conclusive. No change has been made to this final rule in this regard.

Request To Include AD 2004-05-19, Amendment 39-13514 (69 FR 10921, 
March 9, 2004; corrected April 13, 2004 (69 FR 19313))

    Europe Airpost requested that we revise the NPRM (77 FR 56170, 
September 12, 2012) to include AD 2004-05-19, Amendment 39-13514 (69 FR 
10921, March 9, 2004; corrected April 13, 2004 (69 FR 19313)), as a 
related AD in paragraph (b) of the NPRM. The commenter stated that the 
new AD will affect AD 2004-05-19 because attach pins having P/Ns 
180A1612-3 and 180A1612-4 could also have been installed as a 
terminating action for AD 2004-05-19.
    We agree with the commenter and have revised paragraph (b) of this 
final rule accordingly.

Request To Allow Re-Installation of Serviceable Attach Pins

    Japan Airlines (JAL) requested that we revise the NPRM (77 FR 
56170, September 12, 2012) to allow for re-installation of attach pins 
having P/N 180A1612-3 and 180A1612-4 that are found to be serviceable. 
JAL agrees that replacement of the attach pins would have to be done 
before 56,000 total flight cycles, but notes that routine maintenance 
inspections of the pins require pin removal prior to the 56,000 flight 
cycle threshold. JAL concluded that when these inspections are 
accomplished prior to that threshold, paragraphs (h) and (i) of the 
NPRM would prohibit re-installation of the pins, even if they are found 
to be serviceable.
    We partially agree with the request. We agree that re-installation 
of the pins having P/Ns 180A1612-3 and 180A1612-4 that have been 
inspected in accordance with Special Structural Inspections of Section 
9, ``Airworthiness Limitations (AWLs) and Certification Maintenance 
Requirements (CMRs),'' of Boeing 737-600/700/700C/800/900/900ER 
Maintenance Planning Data (MPD) Document D626A001-CMR, Revision 09, may 
be acceptable for compliance; however, the commenter did not state 
which revision of the MPD would be used. As numerous revisions of the 
MPD exist and many new revisions are released each year, this approval 
is most effectively

[[Page 22184]]

accomplished using the procedures in paragraph (k) of this AD. No 
change has been made to the AD in this regard.
    We have revised paragraph (h) of this AD to state that airplanes 
having line numbers 1 through 3534 inclusive having an attach pin P/N 
180A1612-3 or 180A1612-4 must be replaced with a new attach pin P/N 
180A1612-7 or 180A1612-8, respectively, prior to the accumulation of 
56,000 total flight cycles on the pin, or within 3,000 flight cycles 
after the effective date of this AD, whichever occurs later.

STC Winglet Comment

    Aviation Partners Boeing stated that the installation of winglets 
per STC ST00830SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se</a>) does 
not affect the accomplishment of the manufacturer's service 
instructions.
    We have added paragraph (c)(2) to this AD to state that 
installation of STC ST00830SE (<a href="http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se">http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se</a>) does 
not affect the ability to accomplish the actions required by this AD. 
Therefore, for airplanes on which STC ST00830SE is installed, a change 
in product AMOC approval request is not necessary to comply with the 
requirements of 14 CFR 39.17. For all other AMOC requests, the operator 
must request approval for an AMOC in accordance with the procedures 
specified in paragraph (k) of this AD.

Other Changes to the NPRM (77 FR 56170, September 12, 2012)

    We have clarified paragraph (i)(1) of this AD to state that on 
certain airplanes installation of an attach pin having P/N 180A1612-3 
or 180A1612-4 is not acceptable for compliance unless the actions 
required by paragraphs (g) and (h) of this AD are accomplished on that 
airplane.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (77 FR 56170, September 12, 2012) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 56170, September 12, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 1,050 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                            Cost per
            Action                  Labor cost           Parts cost          product    Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Inspection and attach pin       39 work-hours x    Up to $6,312..........     $9,627   Up to $10,108,350.
 replacement.                    $85 per hour =
                                 $3,315.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

    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 adding the following new airworthiness 
directive (AD):

2013-07-07 The Boeing Company: Amendment 39-17411; Docket No. FAA-
2012-0933; Directorate Identifier 2012-NM-107-AD.

(a) Effective Date

    This AD is effective May 20, 2013.

(b) Affected ADs

    This AD affects certain requirements of AD 2004-05-19, Amendment 
39-13514 (69 FR 10921, March 9, 2004; corrected April 13, 2004 (69 
FR 19313)).

(c) Applicability

    (1) This AD applies to all The Boeing Company Model 737-600, -
700, -700C, -800, -900, and -900ER series airplanes, certificated in 
any category.
    (2) Installation of Supplemental Type Certificate (STC) 
ST00830SE (http://rgl.faa.

[[Page 22185]]

gov/Regulatory--and--Guidance--Library/rgstc.nsf/0/
408E012E008616A7862578880060456C?OpenDocument&Highlight=st00830se) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST00830SE is 
installed, a ``change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to comply with the 
requirements of 14 CFR 39.17. For all other AMOC requests, the 
operator must request approval for an AMOC in accordance with the 
procedures specified in paragraph (k) of this AD.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by reports of an incorrect procedure used 
to apply the wear and corrosion protective surface coating to attach 
pins of the horizontal stabilizer rear spar. We are issuing this AD 
to prevent premature failure of the attach pins, which could cause 
reduced structural integrity of the horizontal stabilizer to 
fuselage attachment, resulting in loss of control of the airplane.

(f) Compliance

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

(g) Part Number (P/N) Inspection

    For airplanes having line numbers 1 through 3534 inclusive: 
Before the accumulation of 56,000 total flight cycles, or within 
3,000 flight cycles after the effective date of this AD, whichever 
occurs later, inspect to determine the part number of the attach 
pins of the horizontal stabilizer rear spar. A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
part number of the attach pin can be conclusively determined from 
that review.

(h) Replacement

    If, during the inspection required by paragraph (g) of this AD, 
any horizontal stabilizer rear spar attach pin has P/N 180A1612-3 or 
180A1612-4, prior to the accumulation of 56,000 total flight cycles 
on the pin, or within 3,000 flight cycles after the effective date 
of this AD, whichever occurs later, replace with a new attach pin 
having P/N 180A1612-7 or 180A1612-8, respectively, in accordance 
with the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 737-55-1093, dated April 9, 2012.

(i) Parts Installation Limitation and Prohibition

    (1) For airplanes having line numbers 1 through 3534 inclusive: 
As of the effective date of this AD, no person may install an attach 
pin of the horizontal stabilizer rear spar having P/N 180A1612-3 or 
180A1612-4 on any airplane; unless the actions required by paragraph 
(g) and (h) of this AD have been done on that airplane.
    (2) For airplanes having line numbers 3535 and subsequent: As of 
the effective date of this AD, no person may install an attach pin 
of the horizontal stabilizer rear spar having P/N 180A1612-3 or 
180A1612-4 on any airplane.

(j) Terminating Action for AD 2004-05-19, Amendment 39-13514 (69 FR 
10921, March 9, 2004; corrected April 13, 2004 (69 FR 19313))

    Accomplishment of the actions required by paragraphs (g) and (h) 
of this AD terminates the requirements of paragraphs (a), (b), (c), 
(d), and (e) of AD 2004-05-19, Amendment 39-13514 (69 FR 10921, 
March 9, 2004; corrected April 13, 2004 (69 FR 19313)) for the rear 
spar attach pins only.

(k) 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 the Related Information 
section of this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#794054383734542a1c180d0d151c54383a36543834363a542b1c080c1c0a0d0a391f1818571e160f"><span class="__cf_email__" data-cfemail="b0899df1fefd9de3d5d1c4c4dcd59df1f3ff9df1fdfff39de2d5c1c5d5c3c4c3f0d6d1d19ed7dfc6">[email&#160;protected]</span></a>.
    (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 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. 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.

(l) Related Information

    For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: 425-917-6440; fax: 425-917-6590; email <a href="/cdn-cgi/l/email-protection#e6888788859fc88b8794958ea6808787c8818990"><span class="__cf_email__" data-cfemail="cba5aaa5a8b2e5a6aab9b8a38badaaaae5aca4bd">[email&#160;protected]</span></a>.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (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 Special Attention Service Bulletin 737-55-1093, dated 
April 9, 2012.
    (ii) Reserved.
    (3) For 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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (4) You may view this service information at 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on March 28, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-08193 Filed 4-12-13; 8:45 am]
BILLING CODE 4910-13-P