Airworthiness Directives; The Boeing Company Airplanes

[Federal Register Volume 81, Number 32 (Thursday, February 18, 2016)]
[Rules and Regulations]
[Pages 8138-8140]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-03217]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3630; Directorate Identifier 2014-NM-253-AD; 
Amendment 39-18397; AD 2016-04-03]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 747-400F series airplanes. This AD was prompted by 
an analysis of the production methods used to increase fatigue 
resistance of the upper closure fittings at the nose cargo door 
portal's C-3 frame, which showed that cracking could start too early to 
be caught in a timely manner by the inspection or maintenance program. 
This AD requires inspections of the upper closure fitting and connected 
strap and doubler at the nose cargo door portal for cracking, and 
related investigative and corrective actions if necessary. We are 
issuing this AD to detect and correct such cracking, which could result 
in sudden decompression and loss of the airplane's structural 
integrity.

DATES: This AD is effective March 24, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of March 24, 
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-2015-
3630.

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-2015-
3630; 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 notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all The Boeing Company 
Model 747-400F series airplanes. The NPRM published in the Federal 
Register on September 15, 2015 (80 FR 55273) (``the NPRM''). The NPRM 
was prompted by a report indicating that an analysis of the production 
methods used to increase fatigue resistance of the upper closure 
fittings at the nose cargo door portal's C-3 frame showed that cracking 
could start too early to be caught in a timely manner by the inspection 
or maintenance program. The upper closure fittings used in the nose 
cargo door portal C-3 frame were shot peened to increase fatigue 
resistance. However, an analysis showed that the increase in

[[Page 8139]]

fatigue resistance was still not enough to ensure that cracking would 
be caught by the inspection program specified in the Boeing 747-400 
maintenance planning data (MPD) document. The NPRM proposed to require 
inspections of the upper closure fitting and connected strap and 
doubler at the nose cargo door portal for cracking, and related 
investigative and corrective actions if necessary. We are issuing this 
AD to detect and correct such cracking, which could result in sudden 
decompression and loss of the airplane's structural integrity.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Boeing supported the NPRM.

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 for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2880, dated 
December 3, 2014. This service information describes procedures for a 
detailed inspection of the upper closure fitting and connected strap 
and doubler, a surface high frequency eddy current (HFEC) inspection of 
the upper closure fitting for cracking, and related investigative and 
corrective actions. 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 affects 38 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....................  9 work-hours x $85 per  $0...............  $765 per           $29,070 per
                                  hour = $765 per                            inspection cycle.  inspection
                                  inspection cycle.                                             cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs or 
replacements that would be required based on the results of the 
inspection. Parts costs could be up to $42,930 per airplane. We have no 
way of determining the number of work hours (because the type of repair 
will vary depending on findings) or the number of aircraft that might 
need the repairs or replacements.

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):

2016-04-03 The Boeing Company: Amendment 39-18397; Docket No. FAA-
2015-3630; Directorate Identifier 2014-NM-253-AD.

(a) Effective Date

    This AD is effective March 24, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all The Boeing Company Model 747-400F series 
airplanes, certificated in any category, as identified in paragraph 
1.A., ``Effectivity,'' of Boeing Alert Service Bulletin 747-53A2880, 
dated December 3, 2014.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a report that an analysis of the 
production methods used to increase fatigue resistance of the upper 
closure fittings at the nose cargo door portal's C-3 frame showed 
that cracking could still start too early to be caught in a timely

[[Page 8140]]

manner by the inspection or maintenance program. We are issuing this 
AD to detect and correct such cracking, which could result in sudden 
decompression and loss of the airplane's structural integrity.

(f) Compliance

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

(g) Inspections and Corrective Actions

    Except as required by paragraph (h) of this AD: At the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2880, dated December 3, 2014, 
do a detailed inspection of the upper closure fitting, strap, and 
doubler and a surface high frequency eddy current (HFEC) inspection 
of the upper closure fitting at the nose cargo door portal for 
cracking, and do all applicable related investigative and corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-53A2880, dated December 3, 2014. 
Repeat the inspections at the time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2880, dated 
December 3, 2014. Do the applicable related investigative and 
corrective actions at the times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2880, dated 
December 3, 2014.

(h) Exceptions to the Service Information

    (1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 747-53A2880, dated December 3, 2014, refers to a 
compliance time ``after the original issue date of this service 
bulletin,'' this AD requires compliance within the specific 
compliance time after the effective date of this AD.
    (2) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 747-53A2880, dated December 3, 
2014, specifies to contact Boeing for appropriate action: Before 
further flight, repair the cracking using a method approved in 
accordance with the procedures specified in paragraph (i) of this 
AD.

(i) 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 (j)(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. For a repair method 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) Except as required by paragraph (h)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (i)(4)(i) and 
(i)(4)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(j) Related Information

    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].

(k) 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 Alert Service Bulletin 747-53A2880, dated December 3, 
2014.
    (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 https://www.myboeingfleet.com.
    (4) You may view this service information 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 February 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-03217 Filed 2-17-16; 8:45 am]
 BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:29:52.283904+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

4b0e65ae3de773f9658f66bf8e1291ee353a0a86429949bb931c3048d380ccb3

Text SHA-256

c31e23862622880613c0f43f67599a26464f809eb5e596d914a100ba899136d1