Airworthiness Directives; Dornier Model 328-300 Series Airplanes, 12406-12408 [05-4413]

Download as PDF 12406 Federal Register / Vol. 70, No. 48 / Monday, March 14, 2005 / Rules and Regulations Disk Replacement for TFE731–3, –3A, –3AR, and –3R Series Engines (h) After the effective date of this AD, for TFE731–3, –3A, –3AR, and –3R series engines with LPT stage 1 disk, P/N 3072351– All, 3073113–All, or 3074103–All, installed, replace the LPT stage 1 disk with a serviceable disk, at next MPI, or at next access to the LPT stage 1 nozzle assembly, or before December 31, 2011, whichever occurs first. Disk Replacement for TFE731–3B and –3BR Series Engines (i) For TFE731–3B and –3BR series engines, do the following: (1) After the effective date of this AD, replace LPT stage 1 disk, P/N 3073497–All, with a serviceable LPT stage 1 disk, at next MPI, or at next access to the LPT stage 1 nozzle assembly, or before December 31, 2011, whichever occurs first. (2) Perform the actions specified in paragraph (i)(1) of this AD, by converting the TFE731–3B and –3BR series engines to a TFE731–3C series engine. This conversion allows the installation of a serviceable LPT stage 1 disk. Optional Terminating Action (j) As optional terminating action to the repetitive inspections required by this AD, replace the applicable LPT stage 1 disk with a more robust serviceable disk. Information on installing a serviceable disk can be found in Honeywell International Inc. SB No. TFE731–72–3704, SB No. TFE731–72–3705, and SB No. TFE731–72–3706, all dated September 15, 2004. approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Definitions (k) For the purposes of this AD: (1) Next access to the LPT stage 1 nozzle assembly is defined as when the lowpressure tie-shaft is unstretched. (2) A serviceable LPT stage 1 disk is defined as a disk having a part number not listed in this AD. (3) A serviceable LPT stage 1 nozzle assembly is defined as an LPT stage 1 nozzle assembly that passes the acceptance referenced in paragraphs (f)(1) and (g)(1) of this AD. (n) You must use the Honeywell Engines and Systems service information specified in Table 1 of this AD to perform the measurements, adjustments, calculations, and replacements required by this AD. The Director of the Federal Register approved the incorporation by reference of the document in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Honeywell Engines and Systems Technical Publications and Distribution, M/S 2101– 201, P.O. Box 52170, Phoenix, AZ 85072– 2170; telephone: (602) 365–2493 (General Aviation), (602) 365–5535 (Commercial Aviation), fax: (602) 365–5577 (General Aviation), (602) 365–2832 (Commercial Aviation), for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001, on the internet at https://dms.dot.gov, 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: https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Table 1 follows: Additional Information (l) For additional information regarding the training and tooling recommended to perform the inspection and adjustment of the LPT stage 1 nozzle assembly, contact Honeywell Engines, Systems & Services, Customer Support Center, M/S 26–06/2102– 323, P.O. Box 29003, Phoenix, AZ 85038– 9003, Telephone: (Domestic) 1–800–601– 3099 (International) 1–602–365–3099, FAX: 1–602–365–3343. Alternative Methods of Compliance (m) The Manager, Los Angeles Aircraft Certification Office, has the authority to Material Incorporated by Reference TABLE 1.—INCORPORATION BY REFERENCE Honeywell Service Bulletin No. Page TFE731–72–3369RWK ............................................................................................................. Related Information (o) None. ACTION: Issued in Burlington, Massachusetts, on March 3, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–4686 Filed 3–11–05; 8:45 am] SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Dornier Model 328–300 series airplanes. This AD requires performing repetitive inspections for discrepancies of the heat pack rotor assembly and rotor drive clips of the brake unit of the main landing gear (MLG), and replacing the assembly if any discrepancy is found. This AD is prompted by reports of cracking and breakage of the heat pack rotor assemblies. We are issuing this AD to find and fix discrepancies of the heat pack rotor assembly of the brake unit of the MLG and consequent loss of braking capability, which could result in the airplane overrunning the runway during take-off or landing. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19568; Directorate Identifier 2004–NM–112–AD; Amendment 39–14000; AD 2005–05–11] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). VerDate jul<14>2003 15:26 Mar 11, 2005 Jkt 205001 This AD becomes effective April 18, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of April 18, 2005. PO 00000 Frm 00006 Fmt 4700 1–2 3 4–5 6–14 Sfmt 4700 Date 6 5 6 5 June 26, 2002. August 9, 2001. June 26, 2002. August 9, 2001. For service information identified in this AD, contact AvCraft Aerospace GmbH, P.O. Box 1103, D– 82230 Wessling, Germany. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2004– 19568; the directorate identifier for this docket is 2004–NM–112–AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Dornier Model 328– 300 series airplanes. That action, ADDRESSES: DATES: Airworthiness Directives; Dornier Model 328–300 Series Airplanes AGENCY: Final rule. Revision E:\FR\FM\14MRR1.SGM 14MRR1 Federal Register / Vol. 70, No. 48 / Monday, March 14, 2005 / Rules and Regulations published in the Federal Register on November 12, 2004 (69 FR 65391), proposed to require performing repetitive inspections for discrepancies of the heat pack rotor assembly and rotor drive clips of the brake unit of the main landing gear (MLG), and replacing the assembly if any discrepancy is found. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been submitted on the proposed AD. Request To Remove Certain Requirements Two commenters advise that the actions specified in the proposed AD are already being done each time the MLG wheel is changed, as specified by job instruction card (JIC) 32–41–10–420– 801–A01 for installing MLG wheels. According to the commenters, that JIC gives specific instructions for inspecting the brake rotor clips and fasteners and examining the rotors for splinters and cracks in the area of the clips. The commenters assert that the proposed AD would merely increase the burden of demonstrating AD compliance at every wheel change, creating more paper work without increasing the safety or reliability of the aircraft. We infer that the commenters find the proposed AD unnecessary and request its withdraws. We do not agree. JIC procedures may vary from operator to operator, and operators are not required to comply with the actions specified in JICs. Therefore, AD action is necessary to ensure the safety of the fleet. therefore, we have not changed the final rule regarding this issue. Conclusion We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance This AD affects about 49 airplanes of U.S. registry. The inspection will take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $3,185, or $65 per airplane, per inspection cycle. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate jul<14>2003 15:26 Mar 11, 2005 Jkt 205001 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 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. Frm 00007 Fmt 4700 Sfmt 4700 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–05–11 Fairchild Dornier GmbH (Formerly Dornier Luftfahrt GmbH): Amendment 39–14000. Docket No. FAA–2004–19568; Directorate Identifier 2004–NM–112–AD. Effective Date (a) This AD becomes effective April 18, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Dornier Model 328– 300 series airplanes; certificated in any category; equipped with a Dunlop brake unit having part number AHA2227–3 or –4. Unsafe Condition 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 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); 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 AD. See the ADDRESSES section for a location to examine the regulatory evaluation. PO 00000 § 39.13 12407 (d) This AD was prompted by reports of cracking and breakage of the heat pack rotor assemblies. We are issuing this AD to find and fix discrepancies of the heat pack rotor assembly of the brake unit of the main landing gear (MLG) and consequent loss of braking capability, which could result in the airplane overrunning the runway during take-off or landing. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections/Replacement if Necessary (f) At the next brake installation or within 24 months after the effective date of this AD, which is first: Accomplish a detailed inspection for discrepancies of the heat pack rotor assembly and rotor drive clips of the brake unit of the MLG by doing all the actions specified in the Accomplishment Instructions of Dornier Service Bulletin SB– 328J–32–169, dated November 20, 2002. If any discrepancy is found, before further flight, replace the heat pack rotor assembly with a new assembly in accordance with the service bulletin. Repeat the inspection thereafter in intervals not to exceed the next brake installation or 24 months, whichever is first. Note 1: Dorner Service Bulletin SB–328J– 32–169 refers to Dunlap Aviation Service Bulletin AHA2227–32–1292, Revision 1, dated July 19, 2002, as an additional source of service information. Note 2: For the purpose of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ E:\FR\FM\14MRR1.SGM 14MRR1 12408 Federal Register / Vol. 70, No. 48 / Monday, March 14, 2005 / Rules and Regulations Alternative Methods of Compliance (AMOCs) (g) The Manager, International Branch, ANM–16, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (h) German airworthiness directive D– 2004–003, dated January 8, 2004, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use Dorner Service Bulletin SB–328J–32–169, including the Price/ Material Information Sheet, dated November 20, 2002, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact AvCraft Aerospace GmbH, P.O. Box 1103, D– 82230 Wessling, Germany. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washngton, DC. Issued in Renton, Washington, on February 28, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–4413 Filed 3–11–05; 8:45 am] BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2003–SW–47–AD; Amendment 39–14009; AD 2005–06–01] RIN 2120–AA64 Airworthiness Directives; Eurocopter France Model EC 155B and EC 155B1 Helicopters Federal Aviation Administration, DOT. ACTION: Final rule. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155B and EC 155B1 helicopters that requires inspecting the chamfer of the stop on the cabin sliding doors (doors) and installing an airworthy stop if the chamfer exceeds a certain length; and prior to each flight, visually checking VerDate jul<14>2003 15:26 Mar 11, 2005 Jkt 205001 the door to determine if it is correctly locked in the open position before flying with the doors open, and checking the locking indicator light and the position of the door handles before flying with the doors closed. This amendment also requires revising the Limitations Section of the Rotorcraft Flight Manual (RFM) to prohibit the opening or closing of a cabin sliding door at airspeeds of 40 or greater knots indicated airspeed (KIAS). This amendment is prompted by a report of a door separating from a helicopter during flight. The actions specified by this AD are intended to prevent separation of a door during flight and damage to the helicopter, resulting in a forced landing or loss of control of the helicopter. DATES: Effective April 18, 2005. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 18, 2005. ADDRESSES: The service information referenced in this AD may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. This information may be examined at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas. FOR FURTHER INFORMATION CONTACT: Charles Harrison, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193–0111, telephone (817) 222–5128, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to include an AD for Eurocopter Model EC 155B and EC 155B1 helicopters was published in the Federal Register on August 19, 2004 (69 FR 51402). That action proposed to require, before further flight, revising the Limitations Section of the RFM to prohibit opening or closing the cabin doors except at speeds of less than 40 KIAS; within the next 50 hours TIS, inspecting the chamfer of the stop of the lower rail aft fitting of the doors, and if the chamfer is greater than 2mm in length, installing an airworthy stop. That action also proposed to require; prior to each flight with a door open, visually checking that the door is correctly locked in the open position; and prior to flight with a door closed, checking that the locking indicator light on the instrument panel is ‘‘off’’ when the door is closed, that the door handles are in the correct closed position when the door is locked, and that the lower locking pin is correctly positioned in its catch. These closed- PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 door checks were proposed to be required until a chamfer that is 2mm or less in length is installed and, in accordance with MOD 0753C48, the mounting support plates are modified and the door micro-switches are adjusted. It was proposed that the modification would be accomplished in accordance with the manufacturer’s service information. It was also proposed that the owner/ operator (pilot) holding at least a private pilot certificate may perform the visual checks required by paragraphs (c) and (d) of the proposed AD and must enter compliance with those paragraphs into the aircraft maintenance records in accordance with 14 CFR 43.11 and 91.417(a)(2)(v). The AD would allow a pilot to perform these checks because they involve only visual checks to ensure that the cabin sliding doors are correctly locked in the open or closed position, and can be performed equally well by a pilot or a mechanic. The Direction Generale De L’Aviation Civile (DGAC), the airworthiness authority for France, notified the FAA that an unsafe condition may exist on Model EC 155B and EC 155B1 helicopters. The DGAC advises that they have issued an AD following the loss in flight of a cabin sliding door. Eurocopter issued Alert Service Bulletin No. 52A015, dated September 8, 2003, which specified a modification (MOD 0753C48) to the micro switch support, and an adjustment to the micro switch to ensure lighting of the instrument panel ‘‘DOORS’’ light in the event of insufficient engagement of the cabin sliding door locking pin in its catch. The FAA did not mandate compliance with this alert service bulletin. Eurocopter has also issued Alert Telex No. 52A013, Revision 1, dated September 24, 2003, which specifies: • Within the next 50 hours time-inservice (TIS), inspecting the length of the chamfer on the stop of the lower rail aft fitting of the cabin sliding doors; • Prior to flight with a cabin sliding door open, visually checking that the door is correctly locked in the open position; • Prior to flight with a cabin sliding door closed, checking that the locking indicator light on the instrument panel is off when the door is closed, and when locking the door, checking that the door handle is in the closed position; and • While in flight, prohibiting the opening or closing of a cabin sliding door at airspeeds of 40 or greater KIAS. The DGAC classified this alert telex as mandatory and issued AD No. F–2003– 345 R1, dated November 12, 2003, to E:\FR\FM\14MRR1.SGM 14MRR1

Agencies

[Federal Register Volume 70, Number 48 (Monday, March 14, 2005)]
[Rules and Regulations]
[Pages 12406-12408]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-4413]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19568; Directorate Identifier 2004-NM-112-AD; 
Amendment 39-14000; AD 2005-05-11]
RIN 2120-AA64


Airworthiness Directives; Dornier Model 328-300 Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Dornier Model 328-300 series airplanes. This AD requires 
performing repetitive inspections for discrepancies of the heat pack 
rotor assembly and rotor drive clips of the brake unit of the main 
landing gear (MLG), and replacing the assembly if any discrepancy is 
found. This AD is prompted by reports of cracking and breakage of the 
heat pack rotor assemblies. We are issuing this AD to find and fix 
discrepancies of the heat pack rotor assembly of the brake unit of the 
MLG and consequent loss of braking capability, which could result in 
the airplane overrunning the runway during take-off or landing.

DATES: This AD becomes effective April 18, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of April 
18, 2005.

ADDRESSES: For service information identified in this AD, contact 
AvCraft Aerospace GmbH, P.O. Box 1103, D-82230 Wessling, Germany.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. This 
docket number is FAA-2004-19568; the directorate identifier for this 
docket is 2004-NM-112-AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain Dornier Model 328-300 series airplanes. That 
action,

[[Page 12407]]

published in the Federal Register on November 12, 2004 (69 FR 65391), 
proposed to require performing repetitive inspections for discrepancies 
of the heat pack rotor assembly and rotor drive clips of the brake unit 
of the main landing gear (MLG), and replacing the assembly if any 
discrepancy is found.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Request To Remove Certain Requirements

    Two commenters advise that the actions specified in the proposed AD 
are already being done each time the MLG wheel is changed, as specified 
by job instruction card (JIC) 32-41-10-420-801-A01 for installing MLG 
wheels. According to the commenters, that JIC gives specific 
instructions for inspecting the brake rotor clips and fasteners and 
examining the rotors for splinters and cracks in the area of the clips. 
The commenters assert that the proposed AD would merely increase the 
burden of demonstrating AD compliance at every wheel change, creating 
more paper work without increasing the safety or reliability of the 
aircraft.
    We infer that the commenters find the proposed AD unnecessary and 
request its withdraws. We do not agree. JIC procedures may vary from 
operator to operator, and operators are not required to comply with the 
actions specified in JICs. Therefore, AD action is necessary to ensure 
the safety of the fleet. therefore, we have not changed the final rule 
regarding this issue.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    This AD affects about 49 airplanes of U.S. registry. The inspection 
will take about 1 work hour per airplane, at an average labor rate of 
$65 per work hour. Based on these figures, the estimated cost of the AD 
for U.S. operators is $3,185, or $65 per airplane, per inspection 
cycle.

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 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 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); 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 AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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):

2005-05-11 Fairchild Dornier GmbH (Formerly Dornier Luftfahrt GmbH): 
Amendment 39-14000. Docket No. FAA-2004-19568; Directorate 
Identifier 2004-NM-112-AD.

Effective Date

    (a) This AD becomes effective April 18, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Dornier Model 328-300 series airplanes; 
certificated in any category; equipped with a Dunlop brake unit 
having part number AHA2227-3 or -4.

Unsafe Condition

    (d) This AD was prompted by reports of cracking and breakage of 
the heat pack rotor assemblies. We are issuing this AD to find and 
fix discrepancies of the heat pack rotor assembly of the brake unit 
of the main landing gear (MLG) and consequent loss of braking 
capability, which could result in the airplane overrunning the 
runway during take-off or landing.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Repetitive Inspections/Replacement if Necessary

    (f) At the next brake installation or within 24 months after the 
effective date of this AD, which is first: Accomplish a detailed 
inspection for discrepancies of the heat pack rotor assembly and 
rotor drive clips of the brake unit of the MLG by doing all the 
actions specified in the Accomplishment Instructions of Dornier 
Service Bulletin SB-328J-32-169, dated November 20, 2002. If any 
discrepancy is found, before further flight, replace the heat pack 
rotor assembly with a new assembly in accordance with the service 
bulletin. Repeat the inspection thereafter in intervals not to 
exceed the next brake installation or 24 months, whichever is first.

    Note 1: Dorner Service Bulletin SB-328J-32-169 refers to Dunlap 
Aviation Service Bulletin AHA2227-32-1292, Revision 1, dated July 
19, 2002, as an additional source of service information.


    Note 2: For the purpose of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''


[[Page 12408]]



Alternative Methods of Compliance (AMOCs)

    (g) The Manager, International Branch, ANM-16, Transport 
Airplane Directorate, FAA, has the authority to approve AMOCs for 
this AD, if requested in accordance with the procedures found in 14 
CFR 39.19.

Related Information

    (h) German airworthiness directive D-2004-003, dated January 8, 
2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (i) You must use Dorner Service Bulletin SB-328J-32-169, 
including the Price/Material Information Sheet, dated November 20, 
2002, to perform the actions that are required by this AD, unless 
the AD specifies otherwise. The Director of the Federal Register 
approves the incorporation by reference of these documents in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the 
service information, contact AvCraft Aerospace GmbH, P.O. Box 1103, 
D-82230 Wessling, Germany. For information on the availability of 
this material at the National Archives and Records Administration 
(NARA), call (202) 741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    You may view the AD docket at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-
401, Nassif Building, Washngton, DC.

    Issued in Renton, Washington, on February 28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-4413 Filed 3-11-05; 8:45 am]
BILLING CODE 4910-13-M
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.