[Federal Register Volume 80, Number 51 (Tuesday, March 17, 2015)]
[Rules and Regulations]
[Pages 13761-13763]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-05788]



[[Page 13761]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0536; Directorate Identifier 2015-CE-004-AD; 
Amendment 39-18116; AD 2015-05-06]
RIN 2120-AA64


Airworthiness Directives; Flugzeugwerke Altenrheim AG (FFA) 
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 
Flugzeugwerke Altenrheim AG (FFA) Models AS 202/15 ``BRAVO'', AS 202/
18A ``BRAVO'', and AS 202/18A4 ``BRAVO'' airplanes. This AD results 
from mandatory continuing airworthiness information (MCAI) issued by 
the aviation authority of another country to identify and correct an 
unsafe condition on an aviation product. The MCAI describes the unsafe 
condition as corrosion on the upper forward fuselage stringers. We are 
issuing this AD to require actions to address the unsafe condition on 
these products.

DATES: This AD is effective March 17, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of March 17, 
2015.
    We must receive comments on this AD by May 1, 2015.

ADDRESSES: You may send comments 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 Gomolzig 
Flugzeug- und Maschinenbau GmbH, Eisenwerkstra[szlig]e 9, 58332 
Schwelm, telephone: +49 (0) 2336 490 330; fax; +49 (0) 2336 490 339; 
email: [email protected]; internet: http://www.gomolzig.de/. You may 
view this referenced service information at the FAA, Small Airplane 
Directorate, 901 Locust, Kansas City, Missouri 64106. For information 
on the availability of this material at the FAA, call (816) 329-4148. 
It is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-0536.

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-
0536; 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 (telephone 
(800) 647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: 
[email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2015-0023-E, dated February 18, 2015, (referred to after this as 
``the MCAI''), to correct an unsafe condition for Flugzeugwerke 
Altenrheim AG (FFA) Models AS 202/15 ``BRAVO'', AS 202/18A ``BRAVO'', 
and AS 202/18A4 ``BRAVO'' airplanes. The MCAI states:

    Heavy corrosion was reportedly discovered on an AS 202 
aeroplane, between the forward (FWD) windshield frame angle and the 
upper FWD stringer, left hand (LH) and right hand (RH). The 
corrosion was found underneath the removed windshield frame. 
Corrosion was not detected during a general visual inspection from 
below.
    This condition, if not detected and corrected, could lead to 
failure of the FWD upper stringer, which reduces the structural 
integrity of the affected area.
    To address this potential unsafe condition, Gomolzig Flugzeug- 
und Maschinenbau GmbH (GFM), acting on behalf of the TC holder, have 
issued Service Bulletin (SB) No. 2015-1 to provide inspection 
instructions.
    For the reasons described above, this AD requires repetitive 
inspections of the upper FWD stringer (LH and RH) structure for 
signs of corrosion and, depending on the findings, the 
accomplishment of applicable corrective action(s).
    This AD is considered to be an interim action and further AD 
action may follow.

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2015-0536.

Relevant Service Information Under 1 CFR Part 51

    Gomolzig Flugzeug- und Maschinenbau GmbH has issued Service 
Bulletin GFM SB 2015-1, dated February 5, 2015. The actions described 
in this service information are intended to correct the unsafe 
condition identified in the MCAI. The Gomolzig Flugzeug- und 
Maschinenbau GmbH service bulletin describes procedures for inspecting 
the upper forward stringer (LH and RH) structure for signs of corrosion 
and making all necessary repairs. This service information is 
reasonably available; see ADDRESSES for ways to access this service 
information.

FAA's Determination and Requirements of the AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have notified us of the unsafe condition described in the MCAI and 
service information referenced above. We are issuing this AD because we 
evaluated all information provided by the State of Design Authority and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design.
    This AD is considered an interim action. After issuing this AD, we 
may initiate further AD action to require a possible terminating action 
for the 12-month repetitive inspections.

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 
corrosion on the upper forward fuselage stringers could cause them to 
fail, which could result in reduced structural integrity of the 
windshield frame. Therefore, we determined that notice and opportunity 
for public comment before issuing this AD are impracticable and that 
good cause exists for making this amendment effective in fewer than 30 
days.

[[Page 13762]]

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-0536; Directorate 
Identifier 2015-CE-004-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 1 product of U.S. registry. We 
also estimate that it will take about 6 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour.
    Based on these figures, we estimate the cost of the AD on U.S. 
operators to be $510.
    In addition, we estimate that any necessary follow-on actions will 
take about 20 work-hours and require parts costing $1,000, for a cost 
of $2,700 per product. We have no way of determining at this time if 
the affected airplane may need these actions.

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 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 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.

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 AD:

2015-05-06 Flugzeugwerke Altenrheim AG (FFA): Amendment 39-18116; 
Docket No. FAA-2015-0536; Directorate Identifier 2015-CE-004-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective March 17, 
2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Flugzeugwerke Altenrheim AG (FFA) Models AS 
202/15 ``BRAVO'', AS 202/18A ``BRAVO'', and AS 202/18A4 ``BRAVO'' 
airplanes, all serial numbers, certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of corrosion found on the upper 
forward windshield frame angle and the upper forward stringer. We 
are issuing this AD to detect and correct corrosion on the left-hand 
(LH) and the right-hand (RH) upper forward fuselage stringers. If 
not detected and corrected, this condition could lead to failure of 
the LH and/or the RH upper forward fuselage stringers, which could 
result in reduced structural integrity of the windshield frame.

(f) Actions and Compliance

    Unless already done, do the following actions.
    (1) Before further flight after March 17, 2015 (the effective 
date of this AD) and thereafter at intervals not to exceed 12 
months, do a detailed visual inspection of the LH and RH forward 
(FWD) upper stringer top side structure for corrosion and any signs 
of damage to the corrosion protection. Do the inspection following 
the Instructions section in Gomolzig Flugzeug- und Maschinenbau GmbH 
Service Bulletin GFM SB 2015-1, dated February 5, 2015.
    (2) If corrosion or any signs of damage to the corrosion 
protection is found during any inspection required in paragraph 
(f)(1) of this AD, before further flight after the inspection where 
corrosion or signs of damage to the corrosion protection is found, 
remove the corrosion at the affected area following the Instructions 
section in Gomolzig Flugzeug- und Maschinenbau GmbH Service Bulletin 
GFM SB 2015-1, dated February 5, 2015.
    (3) If corrosion is found during any inspection required in 
paragraph (f)(1) of this AD that exceeds the allowable limits 
specified in paragraph 1.f of the Instructions section in Gomolzig 
Flugzeug- und Maschinenbau GmbH Service Bulletin GFM SB 2015-1, 
dated February 5, 2015, before further flight after the inspection 
where corrosion is found that exceeds the allowable limits, contact 
Gomolzig Flugzeug- und Maschinenbau GmbH at the address specified in 
paragraph (i)(3) of this AD for an FAA-approved repair scheme and 
incorporate the repair.
    (4) Within 30 days after doing the initial inspection required 
in paragraph (f)(1) of this AD, report the results, including 
findings of no corrosion, to Gomolzig Flugzeug- und Maschinenbau 
GmbH at the address specified in paragraph (i)(3) of this AD using 
page 5 of Gomolzig Flugzeug- und Maschinenbau GmbH Service Bulletin 
GFM SB 2015-1, dated February 5, 2015.

(g) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
Standards Office, FAA, has the authority to approve AMOCs for this 
AD, if requested using the procedures found in 14 CFR 39.19. Send 
information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4059; fax: (816) 329-4090; email: 
[email protected]. Before using any approved AMOC on any airplane

[[Page 13763]]

to which the AMOC applies, notify your appropriate principal 
inspector (PI) in the FAA Flight Standards District Office (FSDO), 
or lacking a PI, your local FSDO.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, 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.

(g) Special Flight Permit

    In accordance with 14 CFR 39.23, a single flight is allowed to a 
location where the initial inspection required in paragraph (f)(1) 
of this AD can be done provided the following limitations are 
adhered to:
    (1) No aerobatic maneuvers.
    (2) Normal category maneuvering load factors must not exceed 
+3.8g/-1.9g.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2015-0023-E, dated February 18, 2015, for related information. You 
may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2015-0536.

(i) 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) Gomolzig Flugzeug- und Maschinenbau GmbH Service Bulletin 
GFM SB 2015-1, dated February 5, 2015.
    (ii) Reserved.
    (3) For Gomolzig Flugzeug- und Maschinenbau GmbH service 
information identified in this AD, contact Gomolzig Flugzeug- und 
Maschinenbau GmbH, Eisenwerkstra[szlig]e 9, 58332 Schwelm, 
telephone: +49 (0) 2336 490 330; fax; +49 (0) 2336 490 339; email: 
[email protected]; internet: http://www.gomolzig.de/.
    (4) You may view this referenced service information at the FAA, 
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. 
For information on the availability of this material at the FAA, 
call (816) 329-4148. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2015-0536.
    (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 Kansas City, Missouri on March 4, 2015.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-05788 Filed 3-16-15; 8:45 am]
 BILLING CODE 4910-13-P