[Federal Register Volume 73, Number 153 (Thursday, August 7, 2008)]
[Proposed Rules]
[Pages 45898-45900]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-18225]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0850; Directorate Identifier 2007-NM-342-AD]
RIN 2120-AA64


Airworthiness Directives; Fokker Model F.28 Mark 0100 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed 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:
* * * * *

    During recent inspections it was found that some * * * bolts, 
that connect the horizontal stabilizer control unit actuator with 
the dog-links, were broken. This condition, if not corrected, could 
lead to [the loss of the flight control input connection to the 
horizontal stabilizer and consequent] partial loss of control of the 
aircraft.

* * * * *

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by September 8, 
2008.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations 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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, WA 98057-3356; telephone (425) 227-1137; 
fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0850; 
Directorate Identifier 2007-NM-342-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 proposed AD.

Discussion

    On June 13, 1997, we issued AD 97-13-05, Amendment 39-10051 (62 FR 
34617, June 27, 1997). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 97-13-05, we received reports of inspection 
results indicating that the bolt that connects the horizontal 
stabilizer control unit actuator with the dog-links was broken (one on 
the nut side, and one on the head side). When the bolts fails at the 
nut end, the remaining part of the bolt cannot drop out of the 
connection due to the limited amount of space available between the 
bolt head and plate, and the affected connection is still able to carry 
the system loads. However, if the head side of the bolt fails, then the 
bolt may drop out of the connection.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2007-0287, dated November 15, 2007 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    In January 1996, Fokker issued Service Bulletin (SB) SBF-100-27-
069 (referencing Menasco, now Goodrich, SB 23100-27-19) to introduce 
an inspection of bolt Part Number (P/N) 23233-1 for cracks after the 
examination of a failed bolt. This Service Bulletin was made 
mandatory by CAA-NL (Civil Aviation Authority--the Netherlands) with 
the issuance of AD BLA 1996-006 (A) [reference corresponding FAA AD 
97-13-05]. Additionally the same SB introduced a lower torque value 
for these bolts.
    During recent inspections it was found that some of these bolts, 
that connect the horizontal stabilizer control unit actuator with 
the dog-links, were broken. This condition, if not corrected, could 
lead to [the loss of the flight control input connection to the 
horizontal stabilizer and consequent] partial loss of control of the 
aircraft.
    Since an unsafe condition has been identified that continues to 
exist or develop on other aircraft of the same type design, this 
Airworthiness Directive supersedes CAA-NL AD 1996-006 and requires 
an integrity check by a re-torque in accordance with SBF-100-27-091 
and the installation of a tie-wrap through the bolt, which will act 
as a retainer for the bolt and nut. The key function for this tie-
wrap is to keep the bolt in place in the event the bolt head fails.

    The corrective action includes replacing any failed bolt (i.e., 
broken or

[[Page 45899]]

loose bolt) with a serviceable bolt. This proposed AD also expands the 
applicability of AD 97-13-05. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Fokker Services B.V. has issued Fokker Service Bulletin SBF-100-27-
091, dated August 31, 2007. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

FAA's Determination and Requirements of This Proposed 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 the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 9 products of U.S. registry. We also estimate that 
it would take about 3 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $2,160, or $240 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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); and
    3. 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 a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-10051 (62 FR 
34617, June 27, 1997) and adding the following new AD:

Fokker Services B.V.: Docket No. FAA-2008-0850; Directorate 
Identifier 2007-NM-342-AD.

Comments Due Date

    (a) We must receive comments by September 8, 2008.

Affected ADs

    (b) The proposed AD supersedes AD 97-13-05, Amendment 39-10051.

Applicability

    (c) This AD applies to Fokker Model F.28 Mark 0100 airplanes, 
certificated in any category, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
Controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    In January 1996, Fokker issued Service Bulletin (SB) SBF-100-27-
069 (referencing Menasco, now Goodrich, SB 23100-27-19) to introduce 
an inspection of bolt Part Number (P/N) 23233-1 for cracks after the 
examination of a failed bolt. This Service Bulletin was made 
mandatory by CAA-NL (Civil Aviation Authority--the Netherlands) with 
the issuance of AD BLA 1996-006 (A) [reference corresponding FAA AD 
97-13-05]. Additionally the same SB introduced a lower torque value 
for these bolts.
    During recent inspections it was found that some of these bolts, 
that connect the horizontal stabilizer control unit actuator with 
the dog-links, were broken. This condition, if not corrected, could 
lead to [the loss of the flight control input connection to the 
horizontal stabilizer and consequent] partial loss of control of the 
aircraft.
    Since an unsafe condition has been identified that continues to 
exist or develop on other aircraft of the same type design, this 
Airworthiness Directive [European Aviation Safety Agency (EASA) 
Airworthiness Directive 2007-0287, dated November 15, 2007] 
supersedes CAA-NL AD 1996-006 and requires an integrity check by a 
re-torque in accordance with SBF100-27-091 and the installation of a 
tie wrap through the bolt, which will act as a retainer for the bolt 
and nut. The key function for this tie-wrap is to keep the bolt in 
place in the event the bolt head fails.

The corrective action includes replacing any failed bolt (i.e., 
broken or loose bolt) with a serviceable bolt.

Actions and Compliance

    (f) Unless already done, within 6 months after the effective 
date of this AD, do the following actions.
    (1) Perform a one-time inspection (integrity check) for failure 
of the lower bolts of the stabilizer control unit dog-links, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-27-091, dated August 31, 2007. If a failed bolt is 
found, before further flight, replace the bolt with a serviceable 
bolt in accordance with the Accomplishment Instructions of the 
service bulletin.

[[Page 45900]]

    (2) Install a tie-wrap through the lower bolts of the stabilizer 
control unit, in accordance with the Accomplishment Instructions of 
Fokker Service Bulletin SBF100-27-091, dated August 31, 2007.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Tom Rodriguez, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, WA 98057-3356; telephone (425) 227-
1137; fax (425) 227-1149. 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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2007-0287, dated November 15, 2007, and Fokker Service 
Bulletin SBF100-27-091, dated August 31, 2007, for related 
information.

    Issued in Renton, Washington, on July 29, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-18225 Filed 8-6-08; 8:45 am]
BILLING CODE 4910-13-P