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[Federal Register Volume 77, Number 32 (Thursday, February 16, 2012)]
[Rules and Regulations]
[Pages 9166-9169]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-3618]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

 [Docket No. FAA-2012-0107; Directorate Identifier 2012-NM-018-AD; 
Amendment 39-16955; AD 2012-03-51]
RIN 2120-AA64

Airworthiness Directives; Airplanes Originally Manufactured by 
Lockheed for the Military as P2V Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
airplanes originally manufactured by Lockheed for the military as P2V 
airplanes. This emergency AD was sent previously to all known U.S. 
owners and operators of these airplanes. This AD requires cleaning of 
the forward lower spar cap between wing stations 40 and 84.5 (right and 
left), and doing a detailed inspection for cracks, working fasteners, 
and other anomalies, including surface damage in the form of a nick, 
gouge, or corrosion; and repairing if necessary. This AD was prompted 
by a report of a significant crack in the principle wing structure. We 
are issuing this AD to detect and

[[Page 9167]]

correct cracks, working fasteners, and other anomalies in the principle 
wing structure, which could cause significant loss of structural 
integrity of the wing.

DATES: This AD is effective March 2, 2012 to all persons except those 
persons to whom it was made immediately effective by Emergency AD 2012-
03-51, issued on February 6, 2012, which contained the requirements of 
this amendment.
    We must receive comments on this AD by April 2, 2012.

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations Office 
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 street address for 
the Docket Operations 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: Roger Caldwell, Aerospace Engineer, 
Denver Aircraft Certification Office, FAA, 26805 East 68th Avenue, 
Denver, CO 80249; phone: 303-342-1086; fax: 303-342-1088; e-mail: 
roger.caldwell@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    On February 6, 2012, we issued Emergency AD 2012-03-51, which 
requires cleaning of the forward lower spar cap between wing stations 
40 and 84.5 (right and left), and doing a detailed inspection for 
cracks, working fasteners, and other anomalies, including surface 
damage in the form of a nick, gouge, or corrosion; and repairing if 
necessary. That AD also requires sending inspection results (both 
positive and negative) to the FAA. This AD was prompted by a report of 
a significant crack in the principle wing structure on a Neptune 
Aviation Service, Inc. Model SP-2H (P2V-7) airplane. A crack 
approximately 24 inches long was found in the left side wing front spar 
and lower skin just outboard of the fuselage side of wing station 40. 
The crack propagated through the wing front spar web, lower chord, and 
wing lower skin through stringer No. 22 and aft to stringer No. 21. The 
cause of the cracking is unknown at this time. This condition, if not 
detected and corrected, could result in significant loss of structural 
integrity of the wing.

FAA's Determination

    We are issuing 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.

AD Requirements

    This AD requires cleaning of the forward lower spar cap between 
wing stations 40 and 84.5 (right and left), and doing a detailed 
inspection for cracks, working fasteners, and other anomalies, 
including surface damage in the form of a nick, gouge, or corrosion; 
and repairing if necessary. This AD also requires sending inspection 
results (both positive and negative) to the FAA.

Interim Action

    We consider this AD interim action. If final action is later 
identified, we might consider further rulemaking then.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because of a 
report of a significant crack in the principle wing structure on a 
Neptune Aviation Service, Inc. Model SP-2H (P2V-7) airplane. This 
condition, if not detected and corrected, could result in significant 
loss of structural integrity of the wing. Therefore, we find that 
notice and opportunity for prior public comment are impracticable and 
that good cause exists for making this amendment effective in less than 
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2012-0107 and 
Directorate Identifier 2012-NM-018-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
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 AD.

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
----------------------------------------------------------------------------------------------------------------
        Action              Labor cost          Parts cost          Cost per product     Cost on U.S.  operators
----------------------------------------------------------------------------------------------------------------
Inspection              Up to 80 work-                   $100   Up to $6,900...........  Up to $262,200.
                         hours x $85 per
                         hour = $6,800.
----------------------------------------------------------------------------------------------------------------

    No definitive data are available for repair costs at this time.

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.

[[Page 9168]]

    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):

2012-03-51 Lockheed (Original Manufacturer): Amendment 39-16955; 
Docket No. FAA-2012-0107; Directorate Identifier 2012-NM-018-AD.

(a) Effective Date

    This AD is effective March 2, 2012 to all persons except those 
persons to whom it was made immediately effective by Emergency AD 
2012-03-51, issued on February 6, 2012, which contained the 
requirements of this amendment.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all of the airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), (c)(5), (c)(6), and (c)(7) of this 
AD, certificated in any category:
    (1) Aero Union Corporation Model SP-2H (P2V-7) airplanes;
    (2) Central Air Service, Inc. Model SP-2H (P2V-7) airplanes;
    (3) Evergreen Air Center Model SP-2H (P2V-7) airplanes;
    (4) Hawkins and Powers Aviation, Inc. Model HP-P2V-7 airplanes;
    (5) Minden Air Corp Model SP-2H (P2V-7) airplanes;
    (6) Neptune Aviation Service, Inc. Model SP-2H (P2V-7) 
airplanes; and
    (7) USDA Forest Service (type certificate previously held by 
U.S. Department of Agriculture) Model P2V-5F (SP-2E) airplanes.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by a report of a significant crack in the 
principle wing structure on a Neptune Aviation Service, Inc. Model 
SP-2H (P2V-7) airplane. We are issuing this AD to detect and correct 
cracks, working fasteners, and other anomalies in the principle wing 
structure, which could cause significant loss of structural 
integrity of the wing.

(f) Compliance

    Comply with this AD within the compliance times specified.

(g) Inspections

    Within one day after the effective date of this AD: Do the 
actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD.
    (1) Gain access to the wing spar box between wing stations 40 
and 84.5 (right and left sides of the airplane) through an access 
panel that allows for inspecting the forward lower spar cap assembly 
and remove or reposition any internal fuel bladder assembly that 
impedes access.
    (2) Clean the exposed surface of the forward lower spar cap 
between wing stations 40 and 84.5 (right and left), and do a 
detailed inspection for cracks, working fasteners, and other 
anomalies, including surface damage in the form of a nick, gouge, or 
corrosion, of the forward lower spar cap between wing stations 40 
and 84.5 (right and left).
    (3) If any crack, working fastener, or other anomaly is found 
during any inspection required by paragraph (g)(2) of this AD, 
before further flight, repair in accordance with a method approved 
by the Manager, Denver Aircraft Certification Office (ACO), FAA. For 
a repair method to be approved by the Manager, Denver ACO, as 
required by this paragraph, the Manager's approval letter must 
specifically refer to this AD.

(h) Definition

    For the purposes of this AD, a detailed inspection is: ``An 
intensive examination of a specific item, installation, or assembly 
to detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at an 
intensity deemed appropriate. Inspection aids such as mirror, 
magnifying lenses, etc., may be necessary. Surface cleaning and 
elaborate procedures may be required.

(i) Reporting

    Within 10 days after doing the inspection required by paragraph 
(g) of this AD: Submit a report of the findings (both positive and 
negative) of the inspections required by paragraph (g) of this AD to 
the Denver ACO, FAA, Attention: Roger Caldwell, 26805 East 68th 
Avenue, Denver, CO 80249; phone: 303-342-1086; fax: 303-342-1088; e-
mail: roger.caldwell@faa.gov. The report must include a detailed 
figure or picture of all cracks and damage and the location, 
orientation, and size of all cracks and damage. The report must also 
include the airplane serial number, the number of landings and 
flight hours on the airplane, and a description of how the airplane 
is operated (e.g., firefighting, photography, etc.).

(j) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(k) Special Flight Permit

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed unless approved in accordance with the 
procedures specified in paragraph (l) of this AD.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Denver 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,

[[Page 9169]]

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.
    (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.

(m) Related Information

    For further information about this AD, contact: Roger Caldwell, 
Aerospace Engineer, Denver Aircraft Certification Office, FAA, 26805 
East 68th Avenue, Denver, CO 80249; phone: 303-342-1086; fax: 303-
342-1088; e-mail: roger.caldwell@faa.gov.

(n) Material Incorporated by Reference

    None.

    Issued in Renton, Washington, on February 9, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-3618 Filed 2-15-12; 8:45 am]
BILLING CODE 4910-13-P
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