81 FR 59532 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 168 (August 30, 2016)

We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, -400D, and -400F series airplanes. This proposed AD was prompted by widespread corrosion damage that was found on the skin inner surface along the upper bulkhead at certain stations between certain stringers. This proposed AD would require repetitive inspections of the fuselage crown skin inner surface, and related investigative and corrective actions if necessary. This AD would also allow for terminating actions for some of the repetitive inspections. We are proposing this AD to detect and correct cracks and corrosion on the crown skin inner surface. If the cracks or corrosion are not repaired, the cracks can rapidly join together and can cause a sudden decompression and loss of structural integrity of the airplane.

[Federal Register Volume 81, Number 168 (Tuesday, August 30, 2016)]
[Proposed Rules]
[Pages 59532-59535]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-20683]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9050; Directorate Identifier 2016-NM-086-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 59533]]


ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 747-400, -400D, and -400F series 
airplanes. This proposed AD was prompted by widespread corrosion damage 
that was found on the skin inner surface along the upper bulkhead at 
certain stations between certain stringers. This proposed AD would 
require repetitive inspections of the fuselage crown skin inner 
surface, and related investigative and corrective actions if necessary. 
This AD would also allow for terminating actions for some of the 
repetitive inspections. We are proposing this AD to detect and correct 
cracks and corrosion on the crown skin inner surface. If the cracks or 
corrosion are not repaired, the cracks can rapidly join together and 
can cause a sudden decompression and loss of structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by October 14, 
2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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-2016-9050.

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-2016-
9050; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Nathan Weigand, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6428; fax: 425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2016-9050; 
Directorate Identifier 2016-NM-086-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We received a report indicating that operators have experienced 
widespread corrosion damage that was found on the skin inner surface 
along the upper bulkhead at station (STA) 1480 between stringers S-15L 
and S-16R, on the fuselage skin inner surface aft of the STA 1350 frame 
between stringers S-15 and S-16R and between stringers S-17 and S-18R, 
and on the skin inner surface aft of the STA 1283 frame between 
stringers S-5L and S-8L. This condition, if not corrected, could result 
in cracks that could rapidly join together and can cause a sudden 
decompression and loss of structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 747-53A2878, dated May 
19, 2016. The service information describes procedures for inspecting 
the fuselage crown skin inner surface body at affected stations, and 
related investigative and corrective actions if necessary. 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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between the Proposed AD and the Service 
Information.'' For information on the procedures and compliance times, 
see this service information at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-9050.
    The phrase ``related investigative actions'' is used in this 
proposed AD. Related investigative actions are follow-on actions that 
(1) are related to the primary action, and (2) further investigate the 
nature of any condition found. Related investigative actions in an AD 
could include, for example, inspections.
    The phrase ``corrective actions'' is used in this proposed AD. 
Corrective actions correct or address any condition found. Corrective 
actions in an AD could include, for example, repairs.

Differences Between the Proposed AD and the Service Information

    Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016, 
specifies to contact the manufacturer for certain instructions, but 
this proposed AD would require accomplishment of repair methods, 
modification deviations, and alteration deviations in one of the 
following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

[[Page 59534]]

Costs of Compliance

    We estimate that this proposed AD affects 53 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost            Cost per product      Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspections and access...............  Up to 815                Up to $69,275..........  Up to $3,671,575.
                                        work[dash]hours x $85
                                        per hour = $69,275.
----------------------------------------------------------------------------------------------------------------

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

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Repairs and on[dash]condition          Up to 1,820              N/A....................  Up to $154,700.
 inspections.                           work[dash]hours x $85
                                        per hour = $154,700.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this proposed 
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

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

The Boeing Company: Docket No. FAA-2016-9050; Directorate Identifier 
2016-NM-086-AD.

(a) Comments Due Date

    We must receive comments by October 14, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 747-400, -400D, and 
-400F series airplanes, certificated in any category, as identified 
in Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by widespread corrosion damage that was 
found on the skin inner surface along the upper bulkhead at certain 
stations between certain stringers. We are issuing this AD to detect 
and correct cracks and corrosion on the crown skin inner surface. If 
the cracks or corrosion are not repaired, the cracks can rapidly 
join together and can cause a sudden decompression and loss of 
structural integrity of the airplane.

(f) Compliance

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

(g) Inspection of the Skin Inner Surface

    At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2878, dated 
May 19, 2016, except as required by paragraph (k)(1) of this AD: Do 
a detailed inspection of the skin inner surface for any missing or 
degraded finish, sign of corrosion, or crack, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2878, dated May 19, 2016. Repeat the inspection thereafter at 
intervals not to exceed the applicable time specified in paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2878, 
dated May 19, 2016, until the actions specified in paragraph (i) of 
this AD have been done.

[[Page 59535]]

(h) Repair of the Skin Inner Surface

    If any damage is found during any inspection required by 
paragraph (g) of this AD, before further flight, do all applicable 
related investigative and correction actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2878, dated May 19, 2016, except as required by paragraph (k)(2) 
of this AD.

(i) Terminating Action

    Modification or repair of the inner skin surfaces in accordance 
with Part 3 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2878, May 19, 2016, terminates the 
repetitive inspections required by paragraph (g) of this AD.

(j) Post Repair Inspection and Repairs

    For airplanes on which a repair or modification has been done in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2878, dated May 19, 2016: Except as required 
by paragraph (k)(1) of this AD, at the applicable time specified in 
table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 747-53A2878, dated May 19, 2016, do detailed inspections to 
detect damage of the repaired or modified areas, and do all 
applicable corrective actions, in accordance with Part 5 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2878, May 19, 2016, except as required by paragraph (k)(2) of 
this AD. Do all applicable corrective actions before further flight. 
Repeat the inspections thereafter at intervals not to exceed the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 747-53A2878, dated May 19, 2016.

(k) Exceptions

    (1) Where Boeing Alert Service Bulletin 747-53A2878, May 19, 
2016, specifies a compliance time ``after the original issue date of 
this service bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.
    (2) If any cracking or corrosion is found during any inspection 
required by this AD, and Boeing Alert Service Bulletin 747-53A2878, 
May 19, 2016, specifies to contact Boeing for appropriate action: 
Before further flight, repair the cracking or corrosion using a 
method approved in accordance with the procedures specified in 
paragraph (l) of this AD.

(l) 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 (m)(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) Except as required by paragraph (k)(1) and (k)(2) of this 
AD: For service information that contains steps that are labeled as 
Required for Compliance (RC), the provisions of paragraphs (l)(4)(i) 
and (l)(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.

(m) Related Information

    (1) For more information about this AD, contact Nathan Weigand, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; 
fax: 425-917-6590; email: [email protected].
    (2) 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. 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.

    Issued in Renton, Washington, on August 18, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20683 Filed 8-29-16; 8:45 am]
 BILLING CODE 4910-13-P