Document ID: FAA-2016-6983-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: RUAG Aerospace Services GmbH Airplanes
Posted Date: 2016-08-26T04:00Z

[Federal Register Volume 81, Number 166 (Friday, August 26, 2016)]
[Rules and Regulations]
[Pages 58829-58831]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20072]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6983; Directorate Identifier 2016-CE-012-AD; 
Amendment 39-18618; AD 2016-17-05]
RIN 2120-AA64

Airworthiness Directives; RUAG Aerospace Services GmbH Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2009-13-04 for 
RUAG Aerospace Services GmbH Models 228-100, 228-101, 228-200, 228-201, 
228-202, and 228-212 airplanes. This AD results from mandatory 
continuing airworthiness information (MCAI) issued by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as excessive wear on the guide pin of the power lever or 
condition lever, which could cause functional loss of the flight idle 
stop. We are issuing this AD to require actions to address the unsafe 
condition on these products.

DATES: This AD is effective September 30, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of September 30, 
2016.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6983; or in person at the Docket Management Facility, U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
    For service information identified in this AD, contact RUAG 
Aerospace Services GmbH, Dornier 228 Customer Support, P.O. Box 1253, 
82231 Wessling, Federal Republic of Germany, telephone: +49 (0) 8153-
30-2280; fax: +49 (0) 8153-30-3030; email: 
custsupport.dornier228@ruag.com; Internet: http://www.ruag.com/. You 
may review copies of the 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 Docket No. FAA-2016-6983.

FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4123; fax: (816) 329-4090; email: 
karl.schletzbaum@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to RUAG Aerospace Services 
GmbH Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 
airplanes. That NPRM was published in the Federal Register on June 1, 
2016 (81 FR 34927), and proposed to supersede AD 2009-13-04, Amendment 
39-15943 (74 FR 29116; June 19, 2009) (``AD 2009-13-04'').
    The NPRM proposed to correct an unsafe condition for the specified 
products and was based on mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country. The MCAI (EASA AD No.: 2009-0031R1) states that:

    Excessive wear on a guide pin of a power lever was detected 
during inspections. The failure of a power lever or condition lever 
guide pin could cause functional loss of the flight idle stop.
    This condition, if not corrected, could lead to inadvertent 
activation of the beta mode in flight, possibly resulting in loss of 
control of the aeroplane.
    Prompted by this finding, RUAG issued Alert Service Bulletin 
(ASB) ASB-228-279 to provide inspection instructions. Consequently, 
EASA issued AD 2009-0031 to require repetitive detailed inspections 
of the guide pins of the power levers and condition levers, and 
replacement of any pin that exceeds the allowable wear-limits.
    Since that AD was issued, further analysis has determined that 
the inspection interval, in case of no pin replacement, can be 
extended and RUAG published Revision 1 of ASB-228-279, which also 
included landings (expressed in this AD as flight cycles--FC) as a 
determining factor.
    For the reason described above, this AD revises EASA AD 2009-
0031, amending the compliance times without changing the technical 
requirements, and also introducing some editorial changes for 
standardization.

    EASA revised the MCAI (EASA AD No.: 2009-0031R2) to incorporate 
changes to the applicability. The FAA had already incorporated these 
changes in the NPRM so no changes to the final rule are necessary.
    The MCAI can be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6983.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (74 FR 29116; June 19, 
2009) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed except for 
minor editorial

[[Page 58830]]

changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (74 FR 29116; June 19, 2009) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (74 FR 29116; June 19, 2009).

Related Service Information Under 1 CFR Part 51

    We reviewed the RUAG Aerospace Services GmbH Dornier 228 Alert 
Service Bulletin No. ASB-228-279, revision 1, dated September 22, 2015. 
The service information describes procedures for repetitive inspections 
of the guide pins of the power and condition levers and replacement of 
those pins 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 of the AD.

Costs of Compliance

    We estimate that this AD will affect 18 products of U.S. registry. 
We also estimate that it would take about 20 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Required parts would cost about $10 per product.
    Based on these figures, we estimate the cost of the AD on U.S. 
operators to be $30,780, or $1,710 per product.

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 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.

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-
6983; 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 the NPRM, 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.

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 removing Amendment 39-15943 (74 FR 
29116; June 19, 2009), and adding the following new AD:

2016-17-05 RUAG Aerospace Services GmbH: Amendment 39-18618; Docket 
No. FAA-2016-6983; Directorate Identifier 2016-CE-012-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective September 
30, 2016.

(b) Affected ADs

    This AD supersedes AD 2009-13-04, Amendment 39-15943 (74 FR 
29116; June 19, 2009) (``AD 2009-13-04'').

(c) Applicability

    This AD applies to RUAG Aerospace Services GmbH Models 228-100, 
228-101, 228-200, 228-201, 228-202, and 228-212 airplanes, all 
serial numbers, certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 76: Engine 
Controls.

(e) Reason

    This AD results from mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as excessive wear 
on the guide pin of the power lever or condition lever, which could 
cause functional loss of the flight idle stop. We are issuing this 
proposed AD to amend the compliance times of the guide pin 
inspections.

(f) Actions and Compliance

    Unless already done, do the following actions in paragraphs 
(f)(1) through (4) of this AD based on a compliance time of hours 
time-in-service (TIS) or flight cycles, whichever occurs first. If 
the flight cycles or hours TIS of the throttle box assembly is 
unknown, use the hours TIS of the airplane to determine the 
compliance time for the inspection.
    (1) For throttle box assemblies with less than 9,600 hours TIS 
or 9,600 flight cycles since installed: Inspect the guide pins of 
the power and condition levers for excessive wear following the 
Accomplishment Instructions in paragraph 2 of RUAG Aerospace 
Services GmbH Dornier 228 Alert Service Bulletin No. ASB-228-279, 
revision 1, dated September 22, 2015, at the following times:
    (i) Initially, unless already done within the last 1,200 hours 
TIS or 1,200 flight cycles as of July 24, 2009 (the effective date 
retained from AD 2009-13-04), before or upon accumulating 9,600 
hours TIS or 9,600 flight cycles, or within the next 100 hours TIS 
or 100 flight cycles after July 24, 2009 (the effective date 
retained from AD 2009-13-04), whichever occurs later, inspect the 
guide pins of the power and condition levers for excessive wear; and
    (ii) Repetitively thereafter within 4,800 hours TIS or 4,800 
flight cycles since any previous inspection in which the power and 
condition levers guide pins were not replaced or within 9,600 hours 
TIS or 9,600 flight cycles, whichever occurs first, since the 
previous inspection in which the power and condition levers guide 
pins were replaced.
    (2) For throttle box assemblies with 9,600 hours TIS or more or 
9,600 flight cycles or more but less than 13,200 hours TIS or

[[Page 58831]]

13,200 flight cycles since installed: Inspect the guide pins of the 
power and condition levers for excessive wear within the next 1,200 
hours TIS or 1,200 flight cycles after July 24, 2009 (the effective 
date retained from AD 2009-13-04) following the Accomplishment 
Instructions in paragraph 2 of RUAG Aerospace Services GmbH Dornier 
228 Alert Service Bulletin No. ASB-228-279, revision 1, dated 
September 22, 2015; and
    (i) Repetitively inspect the guide pins of the power and 
condition levers for excessive wear thereafter within 4,800 hours 
TIS or 4,800 flight cycles since any previous inspection in which 
the power and condition levers guide pins were not replaced; or
    (ii) Repetitively inspect the guide pins of the power and 
condition levers for excessive wear within 9,600 hours TIS or 9,600 
flight cycles since the previous inspection in which the power and 
condition levers guide pins were replaced.
    (3) For throttle box assemblies with 13,200 hours TIS or more or 
13,200 flight cycles or more since installed: Within 100 hours TIS 
or 100 flight cycles after July 24, 2009 (the effective date 
retained from AD 2009-13-04) inspect the guide pins of the power and 
condition levers for excessive wear following the Accomplishment 
Instructions in paragraph 2 of RUAG Aerospace Services GmbH Dornier 
228 Alert Service Bulletin No. ASB-228-279, revision 1, dated 
September 22, 2015, at the following times:
    (i) Initially within the next 100 hours TIS or 100 flight cycles 
after July 24, 2009 (the effective date retained from AD 2009-13-
04); and
    (ii) Repetitively thereafter within 4,800 hours TIS or 4,800 
flight cycles since any previous inspection in which the power and 
condition levers guide pins were not replaced or within 9,600 hours 
TIS or 9,600 flight cycles since the previous inspection in which 
the power and condition levers guide pins were replaced.
    (4) For all throttle box assemblies: Before further flight after 
any inspection required in paragraph (f)(1), (2), or (3) of this AD, 
replace any guide pin that exceeds the acceptable wear-limits as 
defined in paragraph 4.1 of RUAG Aerospace Services GmbH Dornier 228 
Alert Service Bulletin No. ASB-228-279, revision 1, dated September 
22, 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: Karl Schletzbaum, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4123; fax: (816) 329-4090; 
email: karl.schletzbaum@faa.gov. Before using any approved AMOC on 
any airplane 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.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No.: 
2009-0031R1, dated March 29, 2016, and EASA AD No.: 2009-0031R2, 
dated June 28, 2016, for related information. The MCAI can be found 
in the AD docket on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-6983.

(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) RUAG Aerospace Services GmbH Dornier 228 Alert Service 
Bulletin No. ASB-228-279, revision 1, dated September 22, 2015.
    (ii) Reserved.
    (3) For RUAG Aerospace Services GmbH service information 
identified in this AD, contact RUAG Aerospace Services GmbH, Dornier 
228 Customer Support, P.O. Box 1253, 82231 Wessling, Federal 
Republic of Germany, telephone: +49 (0) 8153-30-2280; fax: +49 (0) 
8153-30-3030; email: custsupport.dornier228@ruag.com; Internet: 
http://www.ruag.com/.
    (4) You may view this service information at 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. In addition, you can access this service information 
on the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-6983.
    (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 August 17, 2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20072 Filed 8-25-16; 8:45 am]
 BILLING CODE 4910-13-P