Document ID: FAA-2011-1034-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Agusta S.p.A. Model AB139 and AW139 Helicopters
Posted Date: 2011-10-27T04:00Z

[Federal Register Volume 76, Number 208 (Thursday, October 27, 2011)]
[Rules and Regulations]
[Pages 66623-66625]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-27690]

[[Page 66623]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1034; Directorate Identifier 2011-SW-014-AD; 
Amendment 39-16816; AD 2011-20-06]
RIN 2120-AA64

Airworthiness Directives; Agusta S.p.A. Model AB139 and AW139 
Helicopters

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD) for Agusta S.p.A. (Agusta) Model AB139 and AW139 helicopters. This 
action retains the requirements in the existing AD and adds a daily 
check of the tailboom panels to detect bulging or deformation of the 
tailboom outer skin panels. If there is bulging or deformation, this AD 
requires a mechanic to do a tap inspection for debonding. If the 
debonded area exceeds a certain limit, this AD requires modifying the 
tailboom. Also, when an area of debond does not exceed the limits, this 
AD requires, before further flight, repairing the debonded area of the 
tailboom or replacing the tailboom. This action also adds a tap 
inspection for additional tailboom panels and requires the inspection 
on both sides of the tailboom. This amendment is prompted by the 
determination that more inspections are required and to limit the 
applicability only to those helicopters with tailboom assemblies that 
have not been modified. Modifying the tailboom assembly is terminating 
action for the requirements of this AD. The actions specified in this 
AD are intended to detect damage in the tailboom to prevent failure of 
a tailboom and subsequent loss of control of a helicopter.

DATES: Effective November 14, 2011.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 14, 2011.
    Comments for inclusion in the Rules Docket must be received on or 
before December 27, 2011.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     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.
    You may get the service information identified in this AD from 
Agusta, Via Giovanni Agusta, 520 21017 Cascina Costa di Samarate (VA), 
Italy, telephone 39 0331-229111, fax 39 0331-229605/222595, or at 
http://customersupport.agusta.com/technical_advice.php.
    Examining the Docket: You may examine the docket that contains the 
AD, any comments, and other information 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 Docket Operations office (telephone (800) 647-5527) is 
located in Room W12-140 on the ground floor of the West Building at the 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sharon Miles, Aviation Safety 
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, 
2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5122, 
fax (817) 222-5961.

SUPPLEMENTARY INFORMATION: Based on the European Aviation Safety Agency 
(EASA) AD No. 2009-0198 E, dated September 16, 2009, we issued 
Emergency AD 2009-19-51, to all known U.S. owners and operators of 
Agusta Model AB139 and AW139 helicopters. We then issued a Final rule; 
request for comments for AD 2009-19-51, Amendment 39-16129, on January 
11, 2010 (75 FR 3615, January 22, 2010). That AD requires inspecting 
the tailboom panels for debonding and if the debonding area exceeds a 
certain limit, repairing the tailboom. That action was prompted by a 
Model AW139 helicopter tailboom bending and collapsing during taxiing. 
That condition, if not corrected, could result in failure of a tailboom 
and subsequent loss of control of the helicopter.
    Since issuing AD 2009-19-51, we have determined that additional 
inspections are needed on certain tailboom configurations. This 
determination was based on findings from the previous inspections 
required by AD 2009-19-51. Also, the manufacturer has introduced 
tailboom reinforcement structural retro modification (MOD), part number 
(P/N) 3G5309P01812, to reinforce the structure of the tailboom.
    After reports of debonding of fuselage tailboom panels, EASA, which 
is the Technical Agent for the Member States of the European Union, 
issued the following ADs to correct an unsafe condition for the 
specified Agusta model helicopters:
     No. 2009-0234-E, dated October 28, 2009, introduced 
additional inspections of the tailboom panels.
     No. 2009-0234-E R1, dated October 29, 2009, added some 
serial numbers.
     No. 2011-0019, dated February 3, 2011, limits the 
applicability only to those helicopters with tailboom assemblies that 
have not been modified according to MOD, P/N 3G5309P01812, and requires 
modifying the tailboom assemblies with MOD, P/N 3G5309P01812, and to 
contact Agusta if there is an area of debond that exceeds the specified 
limits.

Related Service Information

    Agusta has issued Alert Bollettino Tecnico (ABT) No. 139-195, 
Revision B, dated February 2, 2010, which supersedes ABT No. 139-193 
and No. 139-194, both dated September 3, 2009. Based on findings from 
the inspections specified in ABT No. 139-193 and No. 139-194 on 
specific tailboom configurations, the revised ABT specifies a tighter 
inspection schedule and more frequent tapping inspections on two 
specific areas. The revised ABT retains the 50-flight hour tapping 
inspection specified by the superseded ABTs for inspecting the affected 
tailboom panels for signs of debonding and contacting the manufacturer 
for repair instructions. EASA classified the revised ABT as mandatory 
and issued AD No. 2009-0234-E, dated October 28, 2009, and subsequently 
2009-0234-E R1, dated October 29, 2009, and 2011-0019 dated February 3, 
2011, to ensure the continued airworthiness of these helicopters.

FAA's Evaluation and Unsafe Condition Determination

    These helicopters have been approved by the aviation authority of 
Italy and are approved for operation in the United States. Pursuant to 
our bilateral agreement with Italy, EASA, their technical 
representative, has notified us of the unsafe condition described in AD 
2011-0019. We are issuing this AD because we evaluated all information 
provided by EASA and determined the unsafe condition exists and is 
likely to

[[Page 66624]]

exist or develop on other helicopters of these same type designs.

Differences Between This AD and the EASA AD

    We refer to flight hours as hours time-in-service (TIS). Also, we 
do not require you to contact the manufacturer. Finally, we require the 
inspection on both sides of the tailboom, and the EASA AD only requires 
the inspection on the right side of the tailboom. We do not require a 
specific part-numbered platform to do the inspections, and the EASA AD 
requires using Platform (CG-07-00), P/N 2004-5007-B or approved 
equivalent.

Comments

    The comment period for AD 2009-19-51 closed on March 23, 2010. We 
have considered the two comments received from one commenter.
    The commenter states that Agusta ABT No. 139-195, Revision A, dated 
October 27, 2009, supersedes ABT No. 139-193 and 139-194, and 
recommends referencing ABT 139-195 in the AD. The commenter also 
recommends relocating Note 1 because the current location in the AD can 
cause confusion.
    We agree with the commenter, but ABT No. 139-195 has been revised 
to Revision B. Therefore, we reference ABT 139-195, Revision B, dated 
February 2, 2010, in this superseding AD. The comment about relocating 
Note 1 is not adopted because the ABT is referenced in the 
accomplishment instructions of this AD rather than in a Note.

FAA's Determination and Requirements of This AD

    This unsafe condition is likely to exist or develop on other 
helicopters of the same type design. Therefore, this AD is being issued 
to detect damage in the tailboom to prevent failure of a tailboom and 
subsequent loss of control of a helicopter. This AD requires a daily 
check of each tailboom panel to detect outer skin bulging or 
deformation of the tailboom. This AD allows a pilot holding at least a 
private pilot certificate to perform this check because it involves 
only a visual check for outer skin bulging or deformation of the 
tailboom and does not require the use of tools and can be performed 
equally well by a pilot or a mechanic. If there is bulging or 
deformation on a skin panel, this AD requires a mechanic to use an 
aluminum hammer, P/N 109-3101-58-2, to tap inspect the area around the 
bulge or deformation for debonding. This AD also requires tap 
inspecting the tailboom panels for debonding at 25-hour TIS intervals 
in certain areas on three part-numbered tail assemblies with certain 
serial numbers and at 50-hour TIS intervals for all affected tail 
assemblies except those that are required to be inspected within this 
25-hour TIS interval. If there is any debonding that is not within the 
acceptable limits, before further flight, installing tailboom 
structural reinforcement MOD, P/N 3G5309P01812, is required. If there 
is any debonding that is within the acceptable limits, before further 
flight, repairing the tailboom is required. Modifying the tailboom per 
MOD, P/N 3G5309P01812, is terminating action for the requirements of 
this AD.
    The short compliance time involved is required because the 
previously described critical unsafe condition can adversely affect the 
controllability and structural integrity of the helicopter. Therefore, 
because a daily check of the tailboom panels for outer skin bulgings or 
deformation and the tailboom panel inspections for debonding at 25-hour 
and 50-hour TIS is a very short time interval, this AD must be issued 
immediately.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Costs of Compliance

    We estimate that this AD will affect about 76 helicopters. We also 
estimate that it will take a minimal amount of time to do the daily 
check and about 2 work-hours per recurring inspection per helicopter to 
inspect the tailboom panels for debonding. The average labor rate is 
$85 per work-hour. Installing MOD, P/N 3G5309P01812, would require 192 
work-hours at a parts cost of $52,300. Based on these figures, assuming 
there are 12 recurring inspections and 8 tailboom modifications, we 
estimate the cost of this AD on U.S. operators is $704,000.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any written data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2011-1034; Directorate 
Identifier 2011-SW-014-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the AD. We will consider all 
comments received by the closing date and may amend the AD in light 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 
with FAA personnel concerning this AD. Using the search function of the 
docket web site, you can find and read the comments to any of our 
dockets, including the name of the individual who sent the comment. You 
may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78).

Regulatory Findings

    We have determined that 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 the 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 to the extent that 
it justifies making a regulatory distinction; 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.
    We prepared an economic evaluation of the estimated costs to comply 
with this AD. See the AD docket to examine the economic evaluation.

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

[[Page 66625]]

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
Reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39-16129; (75 FR 
3615, January 22, 2010), and by adding a new airworthiness directive 
(AD), Amendment 39-16816, to read as follows:

2011-20-06 Agusta S.p.A.: Amendment 39-16816. Docket No. FAA-2011-
1034; Directorate Identifier 2011-SW-014-AD. Supersedes AD 2009-19-
51, Amendment 39-16129; Docket No. FAA-2009-1125, Directorate 
Identifier 2009-SW-50-AD.
    Applicability: Model AB139 and AW139 helicopters, with a tail 
assembly, part number (P/N) 3G5350A00132, 3G5350A00133, 
3G5350A00134, or 3G5350A00135, except those with tailboom 
reinforcement structural retro-modification (MOD), P/N 3G5309P01812, 
installed, certificated in any category.
    Compliance: Required as indicated.
    To detect damage to the tailboom to prevent failure of a 
tailboom and subsequent loss of control of a helicopter, do the 
following:
    (a) For all affected helicopters, before further flight, 
visually check all tailboom panels on both sides of the tailboom for 
skin bulging or deformation. Pay particular attention to the 
previously repaired areas. This visual check may be performed by an 
owner/operator (pilot) holding at least a private pilot certificate 
and must be entered into the helicopter records showing compliance 
with paragraph (a) of this AD in accordance with 14 CFR 43.9(a)(1)-
(4) and 91.417(a)(2)(v).
    (b) If there is bulging or deformation of a tailboom panel skin, 
before further flight, using an aluminum hammer (GF-06-00), P/N 109-
3101-58-2 (aluminum hammer), tap inspect the area around the bulge 
or deformity for debonding. Mark the boundaries of the debond area 
and measure the size of the marked area.
    (c) For helicopters with a tailboom assembly, P/N 3G5350A00132, 
3G5350A00133, or 3G5350A00134, and a serial number (S/N) with a 
prefix of ``A'' up to and including S/N 7/109 for the short nose 
configuration and a S/N with a prefix of ``A'' up to and including 
S/N 7/063 for the long-nose configuration, within 25 hours time-in-
service (TIS) from the last inspection or within 7 days, whichever 
occurs first, unless done previously, and thereafter at intervals 
not to exceed 25 hours TIS, tap inspect each tailboom panel on both 
sides of the tailboom in AREAs 3 and 5 for debonding, using an 
aluminum hammer as depicted in Figure 2 of Agusta Alert Bollettino 
Tecnico No. 139-195, Revision B, dated February 2, 2010 (ABT). 
First, inspect AREA 5 then AREA 3. You do not need to tap inspect 
the longeron area contained in AREA 3. Pay particular attention to 
previously repaired areas.
    (d) For all affected helicopters, except those with tailboom 
assembly part numbers and serial numbers described in paragraph (c) 
of this AD, within 50 hours TIS, unless done previously, and 
thereafter at intervals not to exceed 50 hours TIS, tap inspect each 
tailboom panel on both sides of the tailboom for debonding using an 
aluminum hammer. Pay particular attention to the previously repaired 
areas.
    (e) If there is any debonding, mark the debond area and measure 
the size of the marked area.
    (f) Before further flight, install tailboom structural 
reinforcement per MOD, P/N 3G5309P01812; if:
    (1) The mathematical area of a single debond is equal to or 
greater than 320 mm\2\ and is wholly within AREA 3 as depicted in 
Figure 2 of the ABT;
    (2) The mathematical area of a single debond is equal to or 
exceeds 150 mm\2\ if the debond occurs in area 1, 2, 4, or 5 as 
depicted in Figure 2 of the ABT; or
    (3) The distance between the edges of any two debonded areas is 
less than 3 times the largest debond dimension of the two debonded 
areas measured on a line between the centers of the two debonded 
areas; or
    (4) A debond is within 3 mm from any bond joint edge.
    (g) If none of the criteria of paragraphs (f)(1) through (f)(4) 
of this AD are met, before further flight, repair the debonded area 
of the tailboom using FAA engineering approved data and procedures 
or replace the tailboom with an airworthy tailboom.
    (h) Modifying the tailboom per MOD, P/N 3G5309P01812, is 
terminating action for the requirements of this AD.
    (i) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Contact the Manager, Safety Management Group, FAA Attn: Sharon 
Miles, ASW-111, Aviation Safety Engineer, Rotorcraft Directorate, 
Regulations and Guidance Group, 2601 Meacham Blvd, Fort Worth, Texas 
76137, telephone (817) 222-5122, fax (817) 222-5961, for information 
about previously approved alternative methods of compliance.
    (j) The Joint Aircraft System/Component (JASC) Code is 5302: 
Rotorcraft Tailboom.
    (k) The inspections shall be done on both sides of the tailboom 
by following the specified portions of Agusta Alert Bollettino 
Tecnico No. 139-195, Revision B, dated February 2, 2010. The 
Director of the Federal Register approved this incorporation by 
reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Copies may be obtained from Agusta, Via Giovanni Agusta, 520 21017 
Cascina Costa di Samarate (VA), Italy, telephone 39 0331-229111, fax 
39 0331-229605/222595, or at http://customersupport.agusta.com/technical_advice.php. Copies may be inspected at the FAA, Office of 
the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 
663, Fort Worth, Texas, 76137, or 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/code_of_federal_regulations/ibr_locations.html.
    (l) This amendment becomes effective on November 14, 2011.

    Note:  The subject of this AD is addressed in European Aviation 
Safety Agency AD No. 2011-0019, dated February 3, 2011

    .Issued in Fort Worth, Texas, on September 13, 2011.
Lance T. Gant,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011-27690 Filed 10-26-11; 8:45 am]
BILLING CODE 4910-13-P