[Federal Register Volume 76, Number 212 (Wednesday, November 2, 2011)]
[Rules and Regulations]
[Pages 67594-67596]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-28353]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0942; Directorate Identifier 2011-NE-29-AD; 
Amendment 39-16840; AD 2011-21-17]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turboshaft 
Engines

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 all 
General Electric Company (GE) CT7-8A, CT7-8A1, CT7-8E, and CT7-8F5 
turboshaft engines with a fuel filter differential pressure switch, 
part number (P/N) TD028VF0H7Y5 (part of the fuel filter assembly, P/N

[[Page 67595]]

4110T53P06) installed. This AD requires daily visual inspections of the 
fuel filter differential pressure switch for fuel leaks and for 
excessive cracking of the switch mounting flanges due to stress-
corrosion. This AD also requires the installation of a collar kit over 
the fuel filter differential pressure switch as terminating action to 
the daily inspections. This AD was prompted by reports of 47 fuel 
filter differential pressure switches found with stress-corrosion 
cracking of the mounting flanges. We are issuing this AD to prevent 
unrecoverable in-flight engine shutdown, engine bay fire due to fuel 
leakage, and forced landing or accident.

DATES: This AD is effective November 17, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of November 17, 
2011.
    We must receive comments on this AD by December 19, 2011.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact GE-Aviation, 
M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, phone: (513) 552-
3272; email: [email protected]. You may review copies of the service 
information at the FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA. For information on the availability of 
this material at the FAA, call (781) 238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 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: Walter Meibaum, Aerospace Engineer, 
Engine & Propeller Directorate, FAA, 12 New England Executive Park, 
Burlington, MA 01803; phone: (781) 238-7119; fax: (781) 238-7199; 
email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    Since March of 2011, we have received reports of 47 fuel filter 
differential pressure switches found with cracked mounting flanges. The 
pressure switch, P/N TD028VF0H7Y5, is part of the fuel filter assembly, 
P/N 4110T53P06. Investigation has revealed that the two cap screws 
securing the switch to the fuel filter assembly, apply a bending stress 
to the aluminum mounting flanges of the switch. This bending stress, 
coupled with contaminants in the operating environment, can lead to 
stress-corrosion cracking of the mounting flanges on the switch. This 
condition, if not corrected, could result in unrecoverable in-flight 
engine shutdown, engine bay fire due to fuel leakage, and forced 
landing or accident.

Relevant Service Information

    We reviewed GE Alert Service Bulletin (ASB) No. CT7-8-S/B 73-A0007, 
dated July 8, 2011, and ASB No. CT7-8-S/B 73-A0008, dated August 17, 
2011. The service information describes procedures for performing daily 
visual inspections of the fuel filter differential pressure switch for 
fuel leaks and for excessive cracking of the switch mounting flanges, 
and for installing a collar kit over the fuel filter differential 
pressure switch as terminating action to the daily inspections. The 
collar kit will retain the pressure switch from separating from the 
filter head of the fuel filter assembly due to cracks in the pressure 
switch flanges, and will prevent the pressure switch from leaking.

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 accomplishing the actions specified in the service 
information described previously.

FAA's Justification and 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 about 
20% of the affected fuel filter differential pressure switches in 
service have been found cracked. Many of the affected engines are used 
on Sikorsky S-92 helicopters in offshore applications. 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-2011-0942 and 
Directorate Identifier 2011-NE-29-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 will affect 80 engines installed on 
helicopters of U.S. registry. We also estimate that it would take about 
0.1 work-hour per engine to perform a daily visual inspection and about 
0.1 hour to install a collar over the fuel filter differential pressure 
switch. The average labor rate is $85 per work-hour. Required parts 
would cost about $200 per engine. Based on these figures, we estimate 
the total cost of the AD for one visual inspection and installation of 
the collar to U.S. operators to be $17,360.

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:

[[Page 67596]]

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):

2011-21-17 General Electric Company: Amendment 39-16840; Docket No. 
FAA-2011-0942; Directorate Identifier 2011-NE-29-AD.

(a) Effective Date

    This AD is effective November 17, 2011.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CT7-8A, CT7-
8A1, CT7-8E, and CT7-8F5 turboshaft engines, with fuel filter 
differential pressure switch, part number (P/N) TD028VF0H7Y5 (part 
of fuel filter assembly, P/N 4110T53P06), installed.

(d) Unsafe Condition

    This AD was prompted by reports of 47 fuel filter differential 
pressure switches found with stress-corrosion cracking of the 
mounting flanges. We are issuing this AD to prevent unrecoverable 
in-flight engine shutdown, engine bay fire due to fuel leakage, and 
forced landing or accident.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Starting on the effective date of this AD, perform daily 
visual inspections of the fuel filter differential pressure switch 
for leaks and excessive cracking of the mounting flanges.
    (2) Visually inspect in accordance with paragraph 3, 
Accomplishment Instructions, of GE Alert Service Bulletin (ASB) No. 
CT7-8-S/B 73-A0007, dated July 8, 2011.

(f) Mandatory Terminating Action

    (1) As mandatory terminating action to the daily visual 
inspections, within 4 months after the effective date of this AD, 
install collar kit, P/N 59TC02800K1T, over the fuel filter 
differential pressure switch.
    (2) Install the collar kit in accordance with paragraph 3, 
Accomplishment Instructions of GE ASB No. CT7-8-S/B 73-A0008, dated 
August 17, 2011.

(g) Special Flight Permits

    Special flight permits are prohibited.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19.

(i) Related Information

    For more information about this AD, contact Walter Meibaum, 
Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New 
England Executive Park, Burlington, MA 01803; phone: (781) 238-7119; 
fax: (781) 238-7199; email: [email protected].

(j) Material Incorporated by Reference

    You must use the following service information to do the actions 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference 
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following 
service information on the date specified:
    (1) General Electric Company Alert Service Bulletin No. CT7-8-S/
B 73-A0007, dated July 8, 2011, approved for IBR as of November 17, 
2011.
    (2) General Electric Company Alert Service Bulletin No. CT7-8-S/
B 73-A0008, dated August 17, 2011, approved for IBR as of November 
17, 2011.
    (3) For service information identified in this AD, contact GE-
Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, phone: 
(513) 552-3272; email: [email protected].
    (4) You may review copies of the service information at the FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA. For information on the availability of this material 
at the FAA, call (781) 238-7125.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Burlington, Massachusetts, on October 4, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-28353 Filed 11-1-11; 8:45 am]
BILLING CODE 4910-13-P