Airworthiness directives: Raytheon,
[Federal Register: November 20, 2002 (Volume 67, Number 224)]
[Rules and Regulations]
[Page 69996-69999]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20no02-4]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-CE-21-AD; Amendment 39-12955; AD 2002-23-11]
RIN 2120-AA64
Airworthiness Directives; Raytheon Aircraft Company 200, 300, and 1900 Series, and Models F90 and A100-1 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
SUMMARY: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 200, 300, and 1900 series, and Models F90 and A100-1 airplanes. This AD requires you to check the airplane logbook to determine if the elevator(s) has/have been removed from the airplane. If the elevator(s) has/have been removed, this AD also requires you to inspect the elevator balance weight attachment screws for correct length, and, if necessary, install new bolts that are of improved design and rebalance the elevator, depending on the results of the inspection. This AD is the result of the elevator balance weight attachment screws and balance weights being improperly installed when balancing the elevator after it had been removed for repair or repainting. The actions specified by this AD are intended to prevent the balance weight attachment screws from becoming loose. Loose screws could come into contact and interfere with the horizontal stabilizer. This interference could restrict elevator movement and result in loss of elevator pitch control.
DATES: This AD becomes effective on January 10, 2003.
The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 10, 2003.
ADDRESSES: You may get the service information referenced in this AD from Raytheon Aircraft Company, P.O. 9709 E. Central, Kansas 67201- 0085; telephone: (800) 429-5372 or (316) 676-3140. You may view this information at the Federal Aviation Administration (FAA), Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2001-CE-21-AD, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Paul DeVore, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4142; facsimile: (316) 946-4407.
SUPPLEMENTARY INFORMATION:
Discussion
What Events Have Caused This AD?
Raytheon notified FAA of three incidents in which the elevator jammed during takeoff and landing on Models 200, B300, and 1900C airplanes. Investigations showed the cause for the elevator to jam was that the attachment screws and balance weights were not properly installed when the elevators were balanced after they were removed for repair or repainting.
Improperly installed balance weight attachment screws could result in the
[[Page 69997]]
screws becoming loose and contacting and interfering with the horizontal stabilizer. Interference with the horizontal stabilizer could result in restricted elevator movement.
What Is the Potential Impact if FAA Took no Action?
If this condition is not detected and corrected, loose screws could interfere with the horizontal stabilizer, which could cause restricted elevator movement. This condition could result in loss of elevator pitch control.
Has FAA Taken Any Action to This Point?
We issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Raytheon 200, 300, and 1900 series, and Models F90 and A100-1 airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on July 17, 2002 (67 FR 46928). The NPRM proposed to require you to check the airplane logbook to determine if the elevator(s) has/have been removed from the airplane. If the elevator(s) has/have been removed, the NPRM would also require you to inspect the elevator balance weight attachment screws for correct length, and, if necessary, install new bolts that are of improved design and rebalance the elevator, depending on the results of the inspection.
Was the Public Invited To Comment?
The FAA encouraged interested persons to participate in the making of this amendment. The following presents the comment received on the proposal and FAA's response to comment:
Comment Issue: Replace All Elevator Balance Weight Attachment Screws
What Is the Commenter's Concern?
The commenter states that if the purpose of the proposed AD is to prevent the elevator balance weight attachment screws from becoming loose, then all elevator balance weight attachment screws should be replaced with the new bolts, or at the very least, when the elevators are removed for any reason.
What Is FAA's Response to the Concern?
We do not concur with the commenter. According to reports and service history, only elevators that were removed and rebalanced (such as would occur after repainting) were reinstalled with incorrect length screws. We have not received any reports of elevator balance weight attachment screws becoming loose on airplanes in which an elevator had not been removed and rebalanced.
Unless an elevator has been removed and rebalancing is necessary, we have no justification for replacing the elevator balance weight attachment screws with the new bolts when an elevator is removed and reinstalled and rebalancing is not necessary.
In paragraph (d)(5) of the proposed AD, we address installing the new balance weight attachment bolts any time an elevator is removed and rebalancing is necessary.
We have not changed the final rule AD based on this comment.
FAA's Determination
What Is FAA's Final Determination on This Issue?
After careful review of all available information related to the subject presented above, we have determined that air safety and the public interest require the adoption of the rule as proposed except for minor editorial corrections. We have determined that these minor corrections:
--Provide the intent that was proposed in the NPRM for correcting the unsafe condition; and --Do not add any additional burden upon the public than was already proposed in the NPRM.
Cost Impact
How Many Airplanes Does This AD Impact?
We estimate that this AD affects 2,334 airplanes in the U.S. registry.
What Is the Cost Impact of This AD on Owners/operators of the Affected Airplanes?
We estimate the following costs to accomplish the check of the airplane logbook:
Total cost per Total cost on Labor cost
Parts cost
airplane U.S. operators
1 workhour x $60 = $60.................... None required.....................
$60
$140,040
We estimate the following costs to accomplish the inspection of the elevator balance weight attachment screws that will be required based on the results of the logbook check. We have no way of determining the number of airplanes that will need such inspection:
Total cost per Labor cost
Parts cost
airplane
2 workhours x $60 = $120....... None required.........
$120
We estimate the following costs to accomplish the replacement of the elevator balance weight attachment screws that will be required based on the results of the inspection for airplanes in which the logbook check reveals that further inspection is necessary. We have no way of determining the number of airplanes that will need such replacements:
Total cost per Labor cost
Parts cost
airplane
1 workhour x $60 = $60......... $16 per bolt x 2 bolts
$92 per elevator = $32.
[[Page 69998]]
Regulatory Impact
Does This AD Impact Various Entities?
The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.
Does This AD Involve a Significant Rule or Regulatory Action?
For the reasons discussed above, I certify that this action (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. A copy of the final evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption ADDRESSES.
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 Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
-
The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
-
FAA amends Sec. 39.13 by adding a new AD to read as follows:
2002-23-11 Raytheon Aircraft Company: Amendment 39-12955; Docket No. 2001-CE-21-AD.
(a) What airplanes are affected by this AD? This AD affects the following airplane models and serial numbers that are certificated in any category:
Model
Serial Nos.
(1) F90................................ LA-2 through LA-236 (2) A100-1 (U-21J)..................... BB-3 through BB-5 (3) A200 (C-12C)....................... BC-1 through BC-75 and BD-1 through BD-30 (4) A200C (UC-12B)..................... BJ-1 through BJ-66 (5) A200CT (C-12D), (C-12F), (RC-12D), BP-1, BP-7 through BP-11, BP- (FWC-12D), (RC-12G), (RC-12H), (RC- 22, BP-24 through BP-63, FC-1 12K), or (RC-12P).
through FC-3, GR-1 through GR- 19, FE-1 through FE-9, FE-25 through FE-36 (6) B200............................... BB-734, BB-793, BB-829, BB-854 through BB-870, BB-874 through BB-891, BB-894, BB-896 through BB-911, and BB-913 through BB- 1652 (7) B200C.............................. BL-37 through BL-57, BL-61 through BL-72, BL-124 through BL-140 (8) B200C (C-12F), (C-12R), (UC-12M), BL-73 through BL-112, BL-118 or (UC-12F).
through BL-123, BP-64 through BP-71, BU-1 through BU-12, BV- 1 through BV-12, and BW-1 through BW-29 (9) B200CT............................. BN-2 through BN-4, FG-1 and FG- 2 (10) B200T and 200T.................... BT-1 through BT-38 (11) 200............................... BB-2, BB-6 through BB-733, BB- 735 through BB-792, BB-794 through BB-828, BB-830 through BB-853, BB-872, BB-873, BB- 892, BB-893, and BB-912 (12) 200C.............................. BL-1 through BL-23 and BL-25 through BL-36 (13) 200CT............................. BN-1 (14) 300 and 300LW..................... FA-1 through FA-230 and FF-1 through FF-19 (15) B300.............................. FL-1 through FL-241 (16) B300C............................. FM-1 through FM-9 and FN-1 (17) 1900.............................. UA-2 and UA-3 (18) 1900C............................. UB-1 through UB-74 and UC-1 through UC-174 (19) 1900C(C-12J)...................... UD-1 through UD-6 (20) 1900D............................. UE-1 through UE-358
(b) Who must comply with this AD? Anyone who wishes to operate any of the airplanes identified in paragraph (a) of this AD must comply with this AD.
(c) What problem does this AD address? The actions specified by this AD are intended to prevent the balance weight attachment screws from becoming loose. Loose screws could come into contact and interfere with the horizontal stabilizer. This interference could restrict elevator movement and result in loss of elevator pitch control.
(d) What actions must I accomplish to address this problem? To address this problem, you must accomplish the following:
Actions
Compliance
Procedures
(1) Check the airplane logbook Within the next No special to determine whether the
200 hours time-in- procedures elevator(s) has/have been
service (TIS) required to check removed. The owner/operator after January 10, the logbook. holding at least a private
2003 (the
Raytheon pilot certificate as authorized effective date of Mandatory Service by section 43.7 of the Federal this AD).
Bulletin SB 27- Aviation Regulations (14 CFR
3187, Rev. 1, 43.7) may check the airplane
Revised: logbook.
September, 2001, references this airplane logbook check.
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(2) If, by checking the airplane Within the next In accordance with logbook:.
200 hours time-in- the (i) the pilot can positively service (TIS) Accomplishment show that both elevators have after January 10, Instructions never been removed, then the 2003, (the
section of requirements of paragraphs
effective date of Raytheon (d)(2)(ii) and (d)(3) of this this AD).
Mandatory Service AD do not apply. You must make
Bulletin SB 27- an entry into the aircraft
3187, Rev. 1, records that shows compliance
Revised: with this portion of the AD, in
September, 2001. accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (ii) the pilot identifies that the elevator(s) has/have been removed, or if complete records of elevator(s) do not exist, inspect the elevator balance weight attachment screws to determine if they are the correct length. (3) If, during the inspection Not applicable.... In accordance with required in paragraph
the (d)(2)(ii) of this AD, the
Accomplishment elevator balance weight
Instructions attachment screws are found to
section of be the correct length,
Raytheon paragraph (d)(4) of this AD
Mandatory Service does not apply.
Bulletin SB 27- 3187, Rev. 1 Revised: September, 2001. (4) If, during the inspection Prior to further In accordance with required in paragraph
flight after the the (d)(2)(ii) of this AD, the
inspection
Accomplishment elevator balance weight
required in
Instructions attachment screw(s) is/are
paragraph
section of found to be the incorrect
(d)(2)(ii) of Raytheon length, remove and rebalance this AD.
Mandatory Service the elevator(s) by installing
Bulletin SB 27- the balance weights with the
3187, Rev. 1, appropriate new elevator
Revised: balance weight attachment
September, 2001, bolts, part number (P/N) in the
and the range of NAS6703HU12 through
applicable NAS6703HU22, that have drilled
maintenance head and are secured with
manual. safety wire, and re-install the elevator. (5) Do not install, on any
As of January 10, Not applicable. affected airplane, an elevator 2003 (the that has been rebalanced unless effective date of it has been rebalanced by
this AD). installing the balance weights with the appropriate new elevator balance weight attachment bolts, P/N in the range of NAS6703HU12 through NAS6703HU22, that have drilled heads and are secured with safety wire.
Note 1:
The compliance times specified in Raytheon Mandatory Service Bulletin SB 27-3187, Rev. 1, Revised: September, 2001, are different from those required by this AD. The compliance times in this AD take precedence over those in the service bulletin.
(e) Can I comply with this AD in any other way? You may use an alternative method of compliance or adjust the compliance time if:
(1) Your alternative method of compliance provides an equivalent level of safety; and
(2) The Manager, Wichita Aircraft Certification Office (ACO), approves your alternative. Submit your request through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO.
Note 2:
This AD applies to each airplane identified in paragraph (a) of this AD, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/ operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if you have not eliminated the unsafe condition, specific actions you propose to address it.
(f) Where can I get information about any already-approved alternative methods of compliance? Contact Paul DeVore, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4142; facsimile: (316) 946-4407.
(g) What if I need to fly the airplane to another location to comply with this AD? The FAA can issue a special flight permit under Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a location where you can accomplish the requirements of this AD.
(h) Are any service bulletins incorporated into this AD by reference? Actions required by this AD must be done in accordance with Raytheon Mandatory Service Bulletin SB 27-3187, Rev. 1, Revised: September, 2001. The Director of the Federal Register approved this incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may get copies from Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. You may view copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
(i) When does this amendment become effective? This amendment becomes effective on January 10, 2003.
Issued in Kansas City, Missouri, on November 12, 2002. Dorenda D. Baker, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-29132 Filed 11-19-02; 8:45 am]
BILLING CODE 4910-13-P
