AD 2014-22-04

[Federal Register Volume 79, Number 215 (Thursday, November 6, 2014)]
[Rules and Regulations]
[Pages 65885-65887]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2014-26330]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0288; Directorate Identifier 2013-NM-101-AD; 
Amendment 39-18009; AD 2014-22-04]
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 certain 
The Boeing Company Model DC-9-10, DC-9-20, and DC-9-30 series 
airplanes. This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the improved (shot-peened) aft fuselage 
non-ventral pressure bulkhead tee is subject to widespread fatigue 
damage (WFD). This AD requires repetitive inspections for cracking of 
the improved (shot-peened) non-ventral aft pressure bulkhead tees, and 
replacement if necessary. We are issuing this AD to detect and correct 
fatigue cracking of the improved (shot-peened) non-ventral aft pressure 
bulkhead tees connecting the bulkhead web to the fuselage, which could 
result in reduced structural integrity and rapid decompression of the 
airplane.

DATES: This AD is effective December 11, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 11, 
2014.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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.

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> by searching for and locating Docket No. FAA-2014-
0288; 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: Eric Schrieber, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-
627-5348; fax: 562-627-5210; email: <a href="/cdn-cgi/l/email-protection#1673647f753865757e647f737473645670777738717960"><span class="__cf_email__" data-cfemail="a9ccdbc0ca87dacac1dbc0cccbccdbe9cfc8c887cec6df">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain The Boeing Company 
Model DC-9-10, DC-9-20, and DC-9-30 series airplanes. The NPRM 
published in the Federal Register on May 29, 2014 (79 FR 30753). The 
NPRM was prompted by an evaluation by the DAH indicating that the 
improved (shot-peened) aft fuselage non-ventral pressure bulkhead tee 
is subject to WFD. The NPRM proposed to require repetitive inspections 
for cracking of the improved (shot-peened) non-ventral aft pressure 
bulkhead tees, and replacement if necessary. We are issuing this AD to 
detect and correct fatigue cracking of the improved (shot-peened) non-
ventral aft pressure bulkhead tees connecting the bulkhead web to the 
fuselage, which could result in reduced structural integrity and rapid 
decompression of the airplane.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received. Boeing supported the 
NPRM (79 FR 30753, May 29, 2014).

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 30753, May 29, 2014) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 30753, May 29, 2014).

 Costs of Compliance

    We estimate that this AD affects 48 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 65886]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
            Action                  Labor cost       Parts cost    Cost per product    Cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection....................  Up to 148 work-                $0  $12,580 per       Up to $603,840 per
                                 hours x $85 per                    inspection        inspection cycle.
                                 hour = $12,580                     cycle.
                                 per inspection
                                 cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement (per tee).........................  4,000 work[dash]hours x $85 per          $26,000        $366,000
                                                 hour = $340,000.
----------------------------------------------------------------------------------------------------------------

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):


2014-22-04 The Boeing Company: Amendment 39-18009 ; Docket No. FAA-
2014-0288; Directorate Identifier 2013-NM-101-AD.

(a) Effective Date

    This AD is effective December 11, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model DC-9-11, DC-9-12, 
DC-9-13, DC-9-14, DC-9-15, and DC-9-15F airplanes; Model DC-9-21 
airplanes; and Model DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, 
DC-9-33F, DC-9-34, DC-9-34F, and DC-9-32F (C-9A, C-9B) airplanes; 
certificated in any category; equipped with a non-ventral aft 
pressure bulkhead.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an evaluation by the design approval 
holder (DAH) indicating that the improved (shot-peened) non-ventral 
aft pressure bulkhead tee is subject to widespread fatigue damage 
(WFD). We are issuing this AD to detect and correct fatigue cracking 
of the improved (shot-peened) non-ventral aft pressure bulkhead tees 
connecting the bulkhead web to the fuselage, which could result in 
reduced structural integrity and rapid decompression of the 
airplane.

(f) Compliance

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

(g) Definitions

    (1) For the purposes of this AD, the term ``original tee 
section'' refers to the original (non-peened) non-ventral aft 
pressure bulkhead web to fuselage skin attach tee sections.
    (2) For the purposes of this AD, the term ``improved tee 
section'' refers to improved (shot peened) non-ventral aft pressure 
bulkhead web to fuselage skin attach tee sections.

(h) Inspection

    For airplanes on which an improved tee section having P/N 
5910163-257, 5910163-259, 5910163-260, 5910163-261, 5910163-262, 
5910163-263, SR09530001-3, SR09530001-5, SR09530001-6, SR09530001-7, 
SR09530001-8, SR09530001-9, SR09530001-29, SR09530001-30, 
SR09530001-31, SR09530001-32, SR09530001-33, SR09530001-35, 
SR09530056-3, SR09530056-5, SR09530056-6, SR09530056-7, SR09530056-
8, SR09530056-9, SR09530056-11, SR09530056-13, SR09530056-14, 
SR09530056-15, SR09530056-16, SR09530056-17, SR09530056-19, 
SR09530056-21, SR09530056-22, SR09530056-23, SR09530056-24, or 
SR09530056-25, is installed: At the applicable time specified in 
paragraph (i)(1) or (i)(2) of this AD, do a general visual and low 
frequency eddy current (LFEC) inspection (Option I), or a high and 
low

[[Page 65887]]

frequency eddy current inspection (Option II), for cracking of the 
improved tee sections, in accordance with the Accomplishment 
Instructions of McDonnell Douglas DC-9 Alert Service Bulletin A53-
231, Revision 2, dated June 25, 1993, including Service Sketch 
3683D, Revision C, dated July 19, 1989.

(i) Compliance Times

    (1) For Option I and Option II inspections specified in 
paragraph (h) of this AD: If the time of installation of an improved 
tee section having a part number listed in paragraph (h) of this AD 
is known, do the initial inspection required by paragraph (h) of 
this AD within 50,000 flight cycles after installation of the 
improved tee section, or within 1,500 flight cycles after the 
effective date of this AD, whichever occurs later.
    (2) For Option I and Option II inspections specified in 
paragraph (h) of this AD: If the time of installation of an improved 
tee section having a part number identified in paragraph (h) of this 
AD is not known, do the initial inspection required by paragraph (h) 
of this AD before the accumulation of 75,000 total flight cycles, or 
within 1,500 flight cycles after the effective date of this AD, 
whichever occurs later.

(j) Repetitive Inspections

    If no cracking is found during the inspection required by 
paragraph (h) of this AD: Do the actions specified in paragraph 
(j)(1) or (j)(2) of this AD, as applicable, in accordance with the 
Accomplishment Instructions of McDonnell Douglas DC-9 Alert Service 
Bulletin A53-231, Revision 2, dated June 25, 1993, including Service 
Sketch 3683D, Revision C, dated July 19, 1989.
    (1) For Option I: If Option I was used for the inspection 
required by paragraph (h) of this AD, do the actions at the 
applicable intervals, as specified in paragraphs (j)(1)(i), 
(j)(1)(ii), and (j)(1)(iii) of this AD.
    (i) Repeat the LFEC inspection for cracking of the side areas 
above the floor between longerons L7 and L17 on the fuselage left 
and right sides, at intervals not to exceed 2,000 flight cycles.
    (ii) Repeat the general visual inspection for cracking of the 
top and lower areas from longeron L7 left side to L7 right side, and 
lower fuselage longeron L17 to L20 on the fuselage left and right 
sides, at intervals not to exceed 1,500 flight cycles.
    (iii) Repeat the general visual inspection for cracking of the 
bottom areas from longeron L20 left side to L20 right side, at 
intervals not to exceed 3,500 flight cycles.
    (2) For Option II: If Option II was used for the inspection 
required by paragraph (h) of this AD, repeat the high and low eddy 
frequency eddy current inspections for cracking around the entire 
periphery of the fuselage from the forward side of the bulkhead at 
intervals not to exceed 2,500 flight cycles.

(k) Corrective Action and Post-Replacement Inspections

    If any cracking is found during any inspection required by 
paragraph (h) or (j) of this AD: Before further pressurized flight, 
replace each cracked tee section with an airworthy tee section 
having a part number identified in paragraph (h) of this AD, or with 
an original tee section having P/N 5910163-89, 5910163-91, 5910163-
92, 5910163-93, 5910163-94, or 5910163-95, in accordance with the 
Accomplishment Instructions of McDonnell Douglas DC-9 Alert Service 
Bulletin A53-231, Revision 2, dated June 25, 1993, including Service 
Sketch 3683D, Revision C, dated July 19, 1989.
    (1) If the tee section is replaced with an improved tee section 
listed in paragraph (h) of this AD, prior to the accumulation of 
50,000 flight cycles after installation, inspect the tee section in 
accordance with paragraph (h) of this AD and do all applicable 
corrective actions and repetitive inspections in accordance with and 
at the times specified in paragraphs (j) and (k) of this AD.
    (2) If the tee section is replaced with an original tee section 
listed in paragraph (k) of this AD, prior to the accumulation of 
25,000 flight cycles after installation, inspect the tee section in 
accordance with paragraph (h) of this AD and do all applicable 
corrective actions and repetitive inspections in accordance with and 
at the times specified in paragraphs (j) and (k) of this AD.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (m) of this AD. Information may be 
emailed to: <a href="/cdn-cgi/l/email-protection#7a43573b343757363b3b3935573b37353957283f2b2f3f292e293a1c1b1b541d150c"><span class="__cf_email__" data-cfemail="92abbfd3dcdfbfded3d3d1ddbfd3dfddd1bfc0d7c3c7d7c1c6c1d2f4f3f3bcf5fde4">[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, Los Angeles ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane and 14 CFR 25.571, 
Amendment 45, and the approval must specifically refer to this AD.

(m) Related Information

    For more information about this AD, contact Eric Schrieber, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: 
<a href="/cdn-cgi/l/email-protection#86e3f4efe5a8f5e5eef4efe3e4e3f4c6e0e7e7a8e1e9f0"><span class="__cf_email__" data-cfemail="1f7a6d767c316c7c776d767a7d7a6d5f797e7e31787069">[email&#160;protected]</span></a>.

(n) 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) McDonnell Douglas DC-9 Alert Service Bulletin A53-231, 
Revision 2, dated June 25, 1993, including Service Sketch 3683D, 
Revision C, dated July 19, 1989.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; 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 October 28, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-26330 Filed 11-5-14; 8:45 am]
BILLING CODE 4910-13-P